Fuel nozzle and swirler

Abstract

Engines can utilize combustors to combust fuel to drive the engine. Fuel nozzle assemblies can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assemblies can include swirlers and fuel nozzles to supply a mixture of fuel and air for combustion. The use of alternative fuels that combust at higher temperatures or at higher velocities than traditional fuels can meet increased efficiency and meet emissions demands, requiring improved fuel introduction without flame holding or backfiring.

Description

[0001] Cross-reference to related applications

[0002] This application claims priority to Indian Provisional Patent Application No. 202111059696, filed December 21, 2021, and U.S. Patent Application No. 17 / 682,510, filed February 28, 2022, the entire contents of which are incorporated herein by reference. Technical Field

[0003] This topic generally relates to combustors for turbine engines, which have one or both of a fuel nozzle and a swirler. Background Technology

[0004] Engines, such as turbine engines, include a turbine that is driven by the combustion of combustible fuel within the engine's combustor. Engines utilize fuel nozzles to inject combustible fuel into the combustor. Swirlers provide a mixture of fuel and air for efficient combustion. Attached Figure Description

[0005] In the description with reference to the accompanying drawings, a complete and implementable disclosure, including its best mode, is set forth for those skilled in the art, wherein:

[0006] Figure 1 This is a schematic cross-sectional view of an engine according to an exemplary embodiment of the present disclosure.

[0007] Figure 2 It is an exemplary embodiment of the present disclosure for use Figure 1 A schematic cross-sectional view of the engine's burner.

[0008] Figure 3 This is a cross-sectional view of a fuel nozzle assembly including a cyclone with a backward curved lip, according to an exemplary embodiment of the present disclosure.

[0009] Figure 4 This is based on exemplary embodiments of the present disclosure. Figure 3 A cross-sectional view of the fuel nozzle assembly, depicting various geometries used to arrange the lip.

[0010] Figure 5 This is a cross-sectional view of an alternative fuel nozzle including a purge flow behind a cyclone lip, according to an exemplary embodiment of the present disclosure.

[0011] Figure 6 This is a cross-sectional view of an alternative fuel nozzle including a set of axial grooves aligned along the outer diameter of the fuel nozzle in front of the cyclone lip, according to an exemplary embodiment of the present disclosure.

[0012] Figure 7is a perspective view of an axial slot taken along section VII-VII of the cross section of Figure 6 is a perspective view of an axial slot taken along section VII-VII of the cross section of

[0013] Figure 8 is a perspective view of an axial slot taken along section VII-VII of the cross section of

[0014] Figure 9 is a perspective view of an axial slot taken along section VII-VII of the cross section of

[0015] Figure 10 is a perspective view of an axial slot taken along section VII-VII of the cross section of DETAILED DESCRIPTION

[0016] Aspects disclosed herein are directed to fuel nozzle and swirler architecture located within an engine component, and more particularly, to fuel nozzle architecture configured for use with elevated combustion engine temperatures, such as those using hydrogen fuel mixtures. Higher temperature fuels can eliminate carbon emissions, but due to higher flame speeds and high temperatures, can create challenges related to flame holding or flashback. Existing combustors can be susceptible to flame holding or flashback on combustor components when using such high temperature fuels. For illustrative purposes, the present disclosure will be described with respect to a turbine engine for an aircraft having a combustor driving a turbine. However, it will be understood that aspects disclosed herein are not so limited and can be applied to other residential or industrial applications.

[0017] During combustion, engines generate high local temperatures. Fuels that burn hotter than traditional fuels can meet efficiency and carbon emission demands, or by using fuels with higher combustion temperatures can satisfy reduced carbon emissions. Such fuels can include fuels that are lighter than air, such as hydrogen in the gas phase. Existing engines using fuels with higher combustion temperatures and combustion speeds can result in flame holding or flashback on combustor components.

[0018] Reference will now be made in detail to fuel nozzles and swirler architecture, particularly fuel nozzles and swirler architecture for use with turbine engines, one or more examples of which are illustrated in the drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and description have been used to refer to like or similar parts of the disclosure.

[0019] The word "exemplary" is used herein to mean "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 otherwise indicated, all embodiments described herein are to be considered exemplary in nature and not as limiting.

[0020] The terms "forward" and "aft" refer to relative positions within a turbine engine or vehicle and refer to the normal operating attitude of the turbine engine or vehicle. For example, with respect to a turbine engine, forward refers to a position closer to the engine inlet and aft refers to a position closer to the engine nozzle or exhaust.

[0021] As used herein, the term "upstream" refers to a direction opposite to the direction of fluid flow, while the term "downstream" refers to a direction the same as the direction of fluid flow. The terms "forward" or "front" mean in front of something, and "aft" or "back" mean behind something. For example, when used in relation to fluid flow, forward / aft can mean upstream / downstream.

[0022] The term "fluid" can be a gas or a liquid. The term "fluid communication" means that a fluid can establish a connection between designated areas.

[0023] The terms "forward" and "aft" refer to relative positions within a turbine engine or vehicle and refer to the normal operating attitude of the turbine engine or vehicle. For example, with respect to a turbine engine, forward refers to a position closer to the engine inlet and aft refers to a position closer to the engine nozzle or exhaust.

[0024] The term "flame holding" relates to the condition of continuous combustion of a fuel such that a flame is maintained along or proximate to a component, and typically along or proximate to a portion of a fuel nozzle assembly as described herein, and "flashback" relates to the retrogression of a combustion flame in an upstream direction.

[0025] Further, as used herein, the term "radial" or "radially" refers to a direction away from a common center. For example, in the overall context of a turbine engine, radial refers to a direction along a ray extending between a central longitudinal axis of the engine and an outer periphery of the engine.

[0026] All directional references (e.g., radial, axial, proximal, distal, upper, lower, upward, downward, left, right, lateral, front, back, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, aft, etc.) are only used for identification purposes to aid the reader’s understanding of the present disclosure, and do not create limitations, particularly as to the position, orientation, or use of the disclosure described herein. Connection references (e.g., attached, coupled, connected, and joined) are to be construed broadly and will be given their ordinary and accustomed meaning to those skilled in the art unless otherwise explicitly provided. As such, connection references do not necessarily imply that two elements are directly connected to each other and in fixed relation to each other. The exemplary figures are merely intended to generally illustrate the dimensions, locations, sequences, and relative sizes and are subject to variation.

[0027] The singular forms “a,” “an,” and “the” include plural referents unless the context clearly dictates otherwise. Also, as used herein, the term “set” or “a set” of elements can be any number of elements, including only one.

[0028] Approximating language as used herein throughout the description and claims for example, with respect to a quantity, size, or other dimension or characteristic of an element of the disclosure, means that the quantity, size, or other dimension or characteristic is one of, and typically close to or approximates, a stated value due to, for example, manufacturing tolerances, measurement error, or both. Thus, an element or component can be, for example, “about” a stated value, or within a range “about” a stated value. As used herein, the term “about” is meant to encompass a value that is nearly the same as a true value, but also encompasses a value that is slightly different from a true value, due to, for example, measurement error, manufacturing tolerances, or both. For example, a value that is within 1%, 2%, 4%, 5%, 10%, 15%, or 20% of a stated value, or within a range of values that is within 1%, 2%, 4%, 5%, 10%, 15%, or 20% of a range of values, is considered “about” the stated value or the range of values. In this and other contexts, a range limitation is combined and interchanged with a range identified and including all subranges contained therein, unless the context or language indicates otherwise. For example, all ranges disclosed herein encompass the endpoints and the endpoints are combinable independent of one another.

[0029] Combustors introduce fuel from a fuel nozzle, which mixes with air provided by a swirler, and then combusts within the combustor to drive an engine. Increases in efficiency and reductions in emissions have driven a need to use fuels that burn cleaner or at higher temperatures. There is a need to improve the durability of combustors at these operating parameters, such as improving flame control to prevent flame from staying on fuel nozzle and swirler components.

[0030] Figure 1is a schematic view of an engine as an exemplary turbine engine 10. As a non-limiting example, the turbine engine 10 can be used within an aircraft. The turbine engine 10 can 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 such that rotation of one affects rotation of the other and defines an axis of rotation 20 of the turbine engine 10.

[0031] The compressor section 12 can include a low pressure (LP) compressor 22 and a high pressure (HP) compressor 24 fluidly coupled in series with one another. The turbine section 16 can include an LP turbine 28 and an HP turbine 26 fluidly coupled in series with one another. The drive shaft 18 can operably couple the LP compressor 22, the HP compressor 24, the LP turbine 28, and the HP turbine 26 together. Alternatively, the drive shaft 18 can include an LP drive shaft (not shown) and an HP drive shaft (not shown). The LP drive shaft can couple the LP compressor 22 to the LP turbine 28, and the HP drive shaft can couple the HP compressor 24 to the HP turbine 26. An LP train can be defined as a combination of the LP compressor 22, the LP turbine 28, and the LP drive shaft such that rotation of the LP turbine 28 can impart a driving force to the LP drive shaft, which in turn can cause the LP compressor 22 to rotate. An HP train can be defined as a combination of the HP compressor 24, the HP turbine 26, and the HP drive shaft such that rotation of the HP turbine 26 can impart a driving force to the HP drive shaft, which in turn can cause the HP compressor 24 to rotate.

[0032] The compressor section 12 can include a plurality of axially spaced stages. Each stage includes a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary vanes. Compressor blades for a stage of the compressor section 12 can be mounted to a disk, which is mounted to the drive shaft 18. Each set of blades for a given stage can have its own disk. The vanes of the compressor section 12 can be mounted to a casing, which can extend circumferentially around the turbine engine 10. It should be appreciated that the representation of the compressor section 12 is merely schematic and there can be any number of stages. Further, it is contemplated that there can be any other number of components within the compressor section 12.

[0033] Similar to the compressor section 12, the turbine section 16 can 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 a stage of the turbine section 16 can be mounted to a disk, which is mounted to the drive shaft 18. Each set of blades for a given stage can have its own disk. The vanes of the turbine section can be mounted to the casing in a circumferential manner. It is noted that there can be any number of blades, vanes, and turbine stages, as the illustrated turbine section is merely a schematic representation. Further, it is contemplated that there can be any other number of components within the turbine section 16.

[0034] The combustion section 14 can be serially disposed between the compressor section 12 and the turbine section 16. The combustion section 14 can 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 can 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.

[0035] 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, the air is compressed at the compressor section 12, defining pressurized air. The pressurized air can then flow into the combustion section 14, where the pressurized air is mixed with fuel and ignited, generating combustion gases. The HP turbine 26 extracts some work from these combustion gases, the HP turbine 26 driving 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 is ultimately exhausted from the turbine engine 10 via an exhaust section (not shown) downstream of the turbine section 16. The driving of the LP turbine 28 drives the LP spool to rotate the fan (not shown) and the LP compressor 22. The pressurized air stream and the combustion gases can together define a working airflow that flows through the fan, the compressor section 12, the combustion section 14, and the turbine section 16 of the turbine engine 10.

[0036] Figure 2 depictions of suitable Figure 1A cross-sectional view of a combustor 36 used in the combustion section 14 of the gas turbine engine 10. The combustor 36 can include an annular arrangement of fuel nozzle assemblies 38 for providing fuel to the combustor. It should be appreciated that the fuel nozzle assemblies 38 can be organized as an annular arrangement including a plurality of fuel injectors. The combustor 36 can have a can, can-annular, or annular arrangement depending on the type of engine in which the combustor 36 is located. The combustor 36 can include an annular inner combustor liner 40 and an annular outer combustor liner 42, a dome assembly 44 including a dome 46 and a flow diverter 48, which collectively define a combustion chamber 50 about a longitudinal axis 52. At least one fuel injector 54 is fluidly coupled to the combustion chamber 50 to supply fuel to the combustor 36. The fuel injector 54 can be disposed within the dome assembly 44, upstream of a flared cone 56, to define a fuel outlet 58. A swirler can be disposed at the fuel nozzle assembly 38 to swirl incoming air about the fuel exiting the fuel injector 54 and provide a uniform mixture of air and fuel into the combustor 36.

[0037] Figure 3 A fuel nozzle assembly 130 is shown, which is suitable for use as the fuel nozzle assembly 38 in the combustor 36, including a fuel nozzle 132 defining a longitudinal axis 128 and an annular swirler 134 surrounding the fuel nozzle 132. The fuel nozzle 132 can define a fuel passage 136 in which a nozzle cap 138 is disposed relative to the fuel direction, upstream of a nozzle tip 139. The nozzle cap 138 can include a set of openings 141, which can or can not impart swirl or tangential components to the fuel exiting the nozzle tip 139. As shown, the openings 141 are tangentially oriented such that they appear to terminate within the cap 138, however it should be appreciated that the openings 141 extend fully through the cap 138 such that fuel can pass through the cap 138 via the openings 141.

[0038] The swirler 134 includes a front wall 140, a back wall 142, and a center wall 146 with a set of vanes 144 disposed therebetween including a primary set of vanes 144a and a secondary set of vanes 144b extending between the front wall 140 and the center wall 146 and between the back wall 142 and the center wall 146, respectively. The vanes 144 impart tangential swirl to the airflow passing through the swirler 134 prior to discharge. Further, the front wall 140 and the center wall 146 can define a front passage 148 and the center wall 146 and the back wall 142 can define a back passage 150. The primary set of vanes 144a can have a lower swirl number compared to the secondary set of vanes 144b. The lower swirl from the primary set of vanes 144a enables an increased axial velocity component along the outer diameter of the fuel nozzle to prevent flame holding. The higher swirl from the secondary set of vanes 144b enables a higher flow velocity on the diverging exit cone that prevents flame holding. In one non-limiting example, the swirl from the primary set of vanes 144a can be from 0.0 to 0.6, while the swirl from the secondary set of vanes 144b can be from 0.0 to 1.5, while broader ranges are contemplated.

[0039] A lip 152 extends from the vanes 144 at the center wall 146 between the front passage 148 and the back passage 150 in a downstream direction. The lip 152 extends in a radially inward direction and then curves, turning in a rearward direction, relative to the longitudinal extent of the fuel nozzle 132. The lip 152 provides a high velocity component along the fuel nozzle 132, which can reduce or eliminate flame holding and flashback along the fuel nozzle assembly. Further, fuels with high burn rates or temperatures, such as hydrogen, can be used compared to ordinary fuels, while current systems would present durability issues under these operating conditions. The use of hydrogen fuels can provide reduced or eliminated emissions, such as carbon emissions, while maintaining or improving engine efficiency.

[0040] The purge opening 154, which can be arranged as a set of circumferentially arranged openings in one non-limiting example, can extend through the swirler 134 and the front wall 140 and fluidly couple to the swirler 134 through the front wall 140. The purge opening 154 can be angled toward the fuel nozzle 132, while it is further contemplated that the purge opening 154 can include a tangential component such that the purge airflow provided by the purge opening 154 can be similar to the swirl airflow provided from the vanes 144 of the swirler 134, which can reduce shear between the two airflows.

[0041] The rearward curved lip 152 can be positioned between the front passage 148 and the back passage 150 to provide a high velocity component to direct the airflow along the fuel nozzle 132. The curvature of the lip 152 reduces or eliminates a wake flow formed by the lip 152 by utilizing flow from the front passage 148, providing a reduced wake flow or a smaller wake flow distance.

[0042] The passage height H can be defined as the distance between the fuel nozzle 132 and the back wall 142 of the swirler 134 downstream of the lip 152, where the cross-sectional area of the passage height H can extend constant in the back direction along the back wall 142. In the event that the cross-sectional area defined by the passage height is not constant, the passage height H can be defined as the smallest distance between the fuel nozzle 132 and the back wall 142 downstream of the lip 152. In one example, the lip 152 can extend radially inward, toward and relative to the axial extent of the fuel nozzle 132.

[0043] Further, a curvature of the lip 152 can be defined. Specifically, the lip 152 can extend at a 0 degree angle relative to the radial direction R defined by the axial extent of the fuel nozzle 132. The lip 152 can turn, curving from the axial extent toward the back direction. Additionally, the lip 152 can be arranged oblique relative to the fuel nozzle 132, defining a lip axis 168, which can define an angle 164 between 1 degree and 85 degrees relative to the radial axis R, while such a curvature would deviate 5 degrees from an axis parallel to the longitudinal axis 128. Additionally, other ranges are contemplated, such as any angle between 90 degrees and 0 degrees (zero degrees). In other examples, it is contemplated that the curvature can vary, such as in the circumferential direction, or in the radial direction along the circumferential axis, which in one non-limiting example can be aligned with or offset from the purge opening 154. For example, such a variation can be + / - 5 degrees, while other or greater ranges are contemplated.

[0044] Figure 4 A lip height, which can be defined as a first height H1, and a swirler passage height can be defined as a second height H2. The first height H1 can be defined as the radial distance between the trailing edge 158 of the vane 144 and the back end 160 of the lip 152 defined along a ray extending from the longitudinal axis 128 of the fuel nozzle 132. The second height H2 can be defined as the radial distance between the fuel nozzle 132 and the back wall 142. In one example, the first height H1 can be defined between -0.9 H2 and 0.9 H2. That is, the first height H1 can be 0.9 times the second height H2 in which the lip 152 is positioned radially outward of the trailing edge 158 of the vane 144, or the first height H1 can be 0.9 times the second height H2 in which the lip 152 is positioned radially inward of the trailing edge 158 of the vane 144. In another example, the lip can extend radially inward from between 0.2 H2 and 0.8 H2, while other or broader ranges are contemplated. Figure 3

[0045] ​In yet another example, the swirler passage length L can be defined as the axial distance between the aft end 160 of the lip 152 and the nozzle tip 156 of the fuel nozzle 132. For example, the length L can be defined as parallel to the fuel nozzle 132. The lip 152 can be sized or arranged such that the swirler passage length L can be between one (1) to six (6) times H2, while other ranges or sizes are contemplated.

[0046] In yet another example, the purge opening 154 can define a purge opening axis 162 as a centerline through the purge opening 154. The purge opening 154 can be arranged such that the purge axis 162 is defined at an angle 166 relative to the longitudinal axis 128 defined by the fuel nozzle 132 or by the Figure 3 In yet another example, the purge opening 154 can define a purge opening axis 162 as a centerline through the purge opening 154. The purge opening 154 can be arranged such that the purge axis 162 is defined at an angle 166 relative to the longitudinal axis 128 defined by the fuel nozzle 132 or by the

[0047] Turning to Figure 5 , the alternative fuel nozzle assembly 200 includes a fuel nozzle 202 and a swirler 204. The swirler 204 includes a forward wall 206 and an aft wall 208, with a set of vanes 210 extending between the forward wall 206 and the aft wall 208. A swirler lip 212 extends from an aft edge 214 of the set of vanes 210. For example, a purge opening 216 can extend axially and can be arranged parallel to the fuel nozzle 202. The purge opening 216 can be arranged forward of the swirler lip 212 such that there is no line of sight of the purge opening 216 when the fuel nozzle assembly 200 is viewed axially opposite the flow direction. In other words, the purge opening 216 or its outlet can be axially aligned with and axially overlapping the swirler lip 212. Eliminating a direct line of sight of the purge opening 216 can reduce or eliminate flashback at the fuel nozzle assembly 200, or its risk to the purge opening 216.

[0048] Figure 6Another alternative fuel nozzle assembly 230 is shown including a fuel nozzle 232 and a swirler 234. The swirler 234 includes a front wall 236 and a back wall 238 with a center wall 240 therebetween defining a primary swirler passage 242 and a secondary swirler passage 244. A set of primary vanes 246 is disposed in the primary swirler passage 242 and a set of secondary vanes 248 is disposed in the secondary swirler passage 244. An annular lip 250 extends from the center wall 240 at the vane sets 246, 248, curving or angling from a radial direction to an axial direction.

[0049] A set of purge openings 252 are formed into the swirler 234 and are partially defined by an outer diameter of the fuel nozzle 232. With brief reference to Figure 7 , it should be appreciated that the purge openings 252 can be formed as a discrete set of openings that can include grooves or slots formed into an inner diameter wall of the swirler 234 extending parallel to the fuel nozzle 232. The cross-sectional shape of the purge openings 252, best seen in Figure 6 , taken through a cross-section VII-VII of Figure 7 , can be semi-circular, while alternative shapes are contemplated in non-limiting examples, such as a torus, an ellipse, a semi-ellipse, a triangle, a square, a circle, or combinations thereof. Additionally, an annular opening extending completely around the fuel nozzle 232 is contemplated. The annular shape of the fuel nozzle 232 can be understood as shown.

[0050] Returning to Figure 6 , in operation, an air flow is provided through the swirler 234 to impart a swirl or tangential component to the air flow in the primary swirler passage 242 and the secondary swirler passage 244. The purge openings 252 provide a high velocity along the outer diameter of the fuel nozzle 232, which can reduce or eliminate flame holding or flashback on the fuel nozzle 232. The higher tangential component in the secondary swirler passage 244 can reduce or eliminate flame holding on the flared cone 218. The purge openings 252 can be arranged tangential, complementary, or equivalent to the tangential swirl imparted by the primary swirler passage 242.

[0051] With reference to Figure 8 , another alternative fuel nozzle assembly 270 includes a fuel nozzle 272 and a swirler 274. The swirler 274 includes a front wall 276, a back wall 278, and a center wall 280 therebetween defining a primary swirler passage 282 and a secondary swirler passage 284. A first set of vanes 286 is disposed in the primary swirler passage 282 and a second set of vanes 288 is disposed in the secondary swirler passage 284.

[0052] A set of purge openings 290 are arranged circumferentially about the swirler 274 forward of the forward wall 276. The purge openings 290 can be coupled to an annular groove 292 formed into the forward wall 276, which can be common to all of the set of purge openings 290. The groove 292 can comprise a circular profile, while in non-limiting examples any profile is contemplated, such as circular, curved, linear, curvilinear, geometric, toroidal, elliptical, square, or combinations thereof. Further, the groove 292 can be shaped to define a tapered cross-sectional area in the direction of flow, providing an increasing velocity component to the flow exiting the groove 292, which can reduce flame holding or flashback at the fuel nozzle 272. Alternatively, it is contemplated that the groove 292 can comprise a constant cross-section or a diverging cross-section. Further, the purge openings 290 can be inclined or angled toward the fuel nozzle 272, while other suitable arrangements are contemplated, such as a radial angular component, an axial angular component, a circumferential angular component, or combinations thereof. Still further, the cross-sectional area can vary in the circumferential direction, which can be related or unrelated to the arrangement of the purge openings 290. The groove 292 can further provide for uniform spreading of the purge flow prior to being supplied to the swirler 274, which can reduce shear turbulence generated from discrete purge opening exits.

[0053] Figure 9 Another alternative fuel nozzle assembly 300 is shown, which can be similar to the fuel nozzle assembly of Figure 8 , except that an annular groove 302 can be fed from a plurality of purge openings 304, which can be in a stacked arrangement 310, stacked in a radial direction relative to a fuel nozzle 306 of the fuel nozzle assembly 300. It should be appreciated that different arrangements of the purge openings 304 can be used to provide a uniform air supply to the annular groove 302, which can be used to provide a circumferentially uniform flow profile to a swirler 308, while using discrete purge openings 304. Discrete or complex geometries can provide for custom air profiles exiting the purge openings to the swirler 308. Such geometries can be used to improve velocity along the fuel nozzle 306 to reduce flame holding on the nozzle tip, or to improve swirl, which can reduce flame holding on the exit cone or combustor liner.

[0054] Figure 10Yet another alternative fuel nozzle assembly 330 is depicted including a fuel nozzle 332 and a swirler 334. The swirler 334 includes a front wall 336 and a back wall 338 with a center wall 340 therebetween defining a first passage 342 and a second passage 344. A first set of vanes 346 is disposed in the first passage 342 and a second set of vanes 348 is disposed in the second passage 344. A lip 350 extends radially inward from the center wall 340 at a trailing edge 352 of the vanes 346, 348. The lip 350 includes a t-shaped profile such that a first portion 354 of the lip 350 extends in a radial direction that separates into a forward portion 356 and a rearward portion 358 that extend forward and rearward, respectively, from the first portion 354.

[0055] The t-shape of the lip 350 defines a constant cross-sectional area in a radial direction from the forward and rearward portions 356, 358 to the fuel nozzle 332. The constant cross-sectional area provides a higher axial velocity component along the outer diameter of the fuel nozzle 332, which can provide for reduced or eliminated flame holding or flashback at the fuel nozzle 332.

[0056] It should be appreciated that fuels with higher combustion temperatures and higher combustion speeds or lighter weight relative to air or other fuels can provide for reduced or eliminated emissions, or improved efficiency without increasing emissions. In one example, a hydrogen fuel or hydrogen-based fuel can be used, which can eliminate carbon emissions without negatively impacting efficiency. Such fuels including hydrogen require better flame control to prevent flame holding or flashback on the combustor hardware. The aspects described herein can increase the durability of the combustor, while existing combustors cannot provide durability for use with such fuels.

[0057] It should be appreciated that the examples used herein are not limited by the specific illustrated examples, and that one skilled in the art will appreciate that aspects from one or more examples can be mixed with aspects from one or more other examples to form examples that can differ from the specific illustrated examples.

[0058] This written description uses examples to disclose the disclosure, including the best mode, and also to enable any person skilled in the art to practice the disclosure, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the disclosure is defined by the claims, and can include other examples that occur to those skilled in the art. Such 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 with insubstantial differences from the literal languages of the claims.

[0059] Further aspects are provided by the subject matter of the following clauses: A turbine engine, comprising: a compressor section, a combustor section, and a turbine section in a serial flow arrangement, the combustor section including a fuel nozzle assembly, the fuel nozzle assembly including: a fuel nozzle terminating at a nozzle tip, the fuel nozzle defining a longitudinal axis and including a fuel passage; a swirler defining a swirler passage, the fuel nozzle disposed with an outlet; a set of vanes disposed within the swirler; and a lip extending downstream from the set of vanes relative to an airflow through the swirler.

[0060] The turbine engine of any of the preceding clauses, wherein the swirler further includes a forward wall and an aft wall, the set of vanes extending between the forward wall and the aft wall.

[0061] The turbine engine of any of the preceding clauses, further comprising a center wall disposed between the forward wall and the aft wall, and wherein the set of vanes includes a first set of vanes extending between the forward wall and the center wall and a second set of vanes extending between the center wall and the aft wall.

[0062] The turbine engine of any of the preceding clauses, wherein the lip extends from the center wall.

[0063] The turbine engine of any of the preceding clauses, wherein the first set of vanes is arranged to impart between 0.0 and 0.6 swirl and the second set of vanes is arranged to impart between 0.0 and 1.5 swirl.

[0064] The turbine engine of any of the preceding clauses, wherein the lip defines a lip height as a radial distance normal to the longitudinal axis from a trailing edge of the set of vanes to an end of the lip.

[0065] The turbine engine of any of the preceding clauses, wherein the swirler passage defines a swirler height as a radial length between the fuel nozzle and the swirler in a direction normal to the longitudinal axis.

[0066] The turbine engine of any of the preceding clauses, wherein the lip height is between -0.9 times the swirler height and 0.9 times the swirler height.

[0067] The turbine engine of any of the preceding clauses, wherein a swirler passage length defines an axial distance between the lip and the nozzle tip, and wherein the lip height is between one times the swirler passage length and six times the swirler passage length.

[0068] The turbine engine of any of the preceding clauses, wherein the lip is curved in a rearward direction.

[0069] The turbine engine of any of the preceding clauses, wherein the lip is angled relative to the longitudinal axis by an angle, and wherein the angle is between 1 degree and 85 degrees.

[0070] The turbine engine of any of the preceding clauses, wherein the lip has a t-shaped profile.

[0071] The turbine engine of any of the preceding clauses, further comprising a purge opening extending through the swirler.

[0072] The turbine engine of any of the preceding clauses, wherein the purge opening is arranged at an angle relative to the longitudinal axis, wherein the angle is between negative ten degrees and 60 degrees.

[0073] The turbine engine of any of the preceding clauses, wherein the purge opening is axially aligned with the lip.

[0074] The turbine engine of any of the preceding clauses, wherein the purge opening further comprises a groove.

[0075] The turbine engine of any of the preceding clauses, wherein the purge opening is arranged as a plurality of stacked purge openings.

[0076] A fuel nozzle assembly comprising: a fuel nozzle defining a longitudinal axis, including a fuel passage terminating at a nozzle tip; a swirler defining a swirler passage, disposed about the fuel nozzle; a set of vanes disposed within the swirler, configured to impart swirl to an airflow passing through the swirler; and a lip extending downstream from the set of vanes relative to the airflow passing through the swirler.

[0077] A method of injecting fuel from a fuel nozzle assembly, the method comprising: injecting an amount of fuel from a fuel nozzle; and providing an amount of air from a swirler along a lip; wherein the lip provides an increased axial velocity component along the fuel nozzle compared to a fuel nozzle assembly without a lip.

[0078] The method of any of the preceding clauses, wherein the lip is curved in a rearward direction.

Claims

1. A turbine engine characterized by, Comprising: a compressor section, a combustor section, and a turbine section in a serial flow arrangement, the combustor section including a fuel nozzle assembly, the fuel nozzle assembly including: a fuel nozzle defining a longitudinal axis and a fuel passage, the fuel nozzle terminating at a nozzle tip and exhausting to the combustor section at the nozzle tip extending through the longitudinal axis; a swirler defining a swirler passage and including a forward wall and an aft wall, a center wall disposed between the forward wall and the aft wall; a set of vanes disposed within the swirler, the set of vanes including a first set of vanes extending between the forward wall and the center wall and a second set of vanes extending between the center wall and the aft wall; and a lip extending from the center wall in a downstream direction relative to airflow through the swirler, the lip terminating at an aft end; the nozzle tip being located aft of the aft end of the lip relative to the longitudinal axis; the aft end of the lip being located forward of the aft wall relative to the longitudinal axis.

2. The turbine engine as defined in claim 1 wherein, wherein the first set of vanes is arranged to impart between 0.0 and 0.6 swirl and the second set of vanes is arranged to impart between 0.0 and 1.5 swirl.

3. The turbine engine of claim 1, wherein, wherein the lip defines a lip height as a radial distance from the set of vanes to an end of the lip that is perpendicular to the longitudinal axis.

4. The turbine engine of claim 3, wherein, wherein the swirler passage defines a swirler height as a radial length between the fuel nozzle and the swirler in a direction perpendicular to the longitudinal axis.

5. The turbine engine of claim 4, wherein, wherein the lip height is between -0.9 times the swirler height and 0.9 times the swirler height.

6. The turbine engine of claim 4, wherein, wherein a swirler passage length is defined as an axial distance between the lip and the nozzle tip, and wherein the lip height is between one times the swirler passage length and six times the swirler passage length.

7. The turbine engine of any one of claims 1 or 3-6, wherein, wherein the lip is curved in an aft direction.

8. The turbine engine of any one of claims 1 or 3-6, wherein, wherein the lip is angled relative to the longitudinal axis by an angle, and wherein the angle is between 1 degree and 85 degrees.

9. The turbine engine of any one of claims 1 or 3-6, wherein, wherein the lip has a T-shaped profile.

10. The turbine engine of any one of claims 1 or 3-6, wherein, further comprising a purge opening extending through the swirler.

11. The turbine engine of claim 10, wherein, wherein the purge opening is arranged at an angle relative to the longitudinal axis, wherein the angle is between negative ten degrees and 60 degrees.

12. The turbine engine of claim 10, wherein, wherein the purge opening is axially aligned with the lip.

13. The turbine engine of claim 10, wherein, wherein the purge opening further comprises a groove.

14. The turbine engine of claim 13, wherein, wherein the purge opening is arranged as a plurality of stacked purge openings.

15. A fuel nozzle assembly, comprising: Comprising: a fuel nozzle defining a longitudinal axis, including a fuel passage that terminates at a nozzle tip and exhausts at the nozzle tip, wherein the nozzle tip is disposed to exhaust to a combustor and extends through the longitudinal axis; a swirler defining a swirler passage, disposed about the fuel nozzle, and including a forward wall and an aft wall, a center wall disposed between the forward wall and the aft wall; a set of vanes disposed within the swirler, the set of vanes including a first set of vanes extending between the forward wall and the center wall and a second set of vanes extending between the center wall and the aft wall; and a lip extending from the center wall in a downstream direction relative to airflow through the swirler, the lip terminating at an aft end; the nozzle tip being located aft of the aft end of the lip relative to the longitudinal axis; the aft end of the lip being located forward of the aft wall relative to the longitudinal axis. wherein the first set of vanes is arranged to impart between 0.0 and 0.6 swirl and the second set of vanes is arranged to impart between 0.0 and 1.5 swirl. wherein the lip defines a lip height as a radial distance from the set of vanes to an end of the lip that is perpendicular to the longitudinal axis. wherein the swirler passage defines a swirler height as a radial length between the fuel nozzle and the swirler in a direction perpendicular to the longitudinal axis. wherein the lip height is between -0.9 times the swirler height and 0.9 times the swirler height. wherein a swirler passage length is defined as an axial distance between the lip and the nozzle tip, and wherein the lip height is between one times the swirler passage length and six times the swirler passage length. wherein the lip is curved in an aft direction. wherein the lip is angled relative to the longitudinal axis by an angle, and wherein the angle is between 1 degree and 85 degrees. wherein the lip has a T-shaped profile. further comprising a purge opening extending through the swirler. wherein the purge opening is arranged at an angle relative to the longitudinal axis, wherein the angle is between negative ten degrees and 60 degrees. wherein the purge opening is axially aligned with the lip. wherein the purge opening further comprises a groove. wherein the purge opening is arranged as a plurality of stacked purge openings. a set of vanes disposed within the swirler configured to impart swirl to an airflow passing through the swirler, the set of vanes including a first set of vanes extending between the front wall and the center wall and a second set of vanes extending between the center wall and the back wall; and a lip extending from the center wall in a downstream direction relative to an airflow passing through the swirler, the lip terminating at a back end; the nozzle tip is located aft of the back end of the lip relative to the longitudinal axis; the back end of the lip is located forward of the back wall relative to the longitudinal axis.

16. A method of injecting fuel from a fuel nozzle assembly, the method comprising: The method comprises: injecting an amount of fuel from a fuel nozzle at a nozzle tip to a combustor, the fuel nozzle defining a longitudinal axis and the nozzle tip extending through the longitudinal axis; and providing an amount of air from a swirler along a lip, wherein the swirler includes a front wall and a back wall, a center wall disposed between the front wall and the back wall; wherein the fuel nozzle assembly includes a set of vanes disposed within the swirler, the set of vanes including a first set of vanes extending between the front wall and the center wall and a second set of vanes extending between the center wall and the back wall wherein the lip extends from the center wall in a downstream direction relative to an airflow passing through the swirler, the lip terminating at a back end, the nozzle tip is located aft of the back end of the lip relative to the longitudinal axis, the back end of the lip is located forward of the back wall relative to the longitudinal axis, the lip provides an increased axial velocity component along the fuel nozzle compared to a fuel nozzle assembly without a lip.

17. The method of claim 16, wherein, wherein the lip is curved in a back direction.

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