Engine 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 a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. Changing the geometry of the swirler can provide improved air supply, which can improve efficiency and flame control.

Description

[0001] Cross-references to related applications

[0002] This application claims priority and interest in U.S. Provisional Patent Application No. 63 / 294,925, filed December 30, 2021, and U.S. Patent Application No. 17 / 692,411, filed March 11, 2022, the entire contents of which are incorporated herein by reference. Technical Field

[0003] This topic generally relates to engine components having one or both of a fuel nozzle and a swirler. Background Technology

[0004] Engines, such as turbine engines that include a turbine, are driven by the combustion of combustible fuel within the engine's combustor. The engine uses fuel nozzles to inject combustible fuel into the combustor. Swirlers provide a mixture of fuel and air to achieve 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 This is based on exemplary embodiments of the present disclosure. Figure 1 A cross-sectional view of the engine's fuel nozzle assembly and cyclone separator, including cyclone separator blades with axial reduction.

[0008] Figure 3 This is a cross-sectional view of an alternative fuel nozzle assembly including a cyclone separator according to an exemplary embodiment of the present disclosure, the cyclone separator having radial blades combined with an axial outlet.

[0009] Figure 4 This is a side view of a swirler for a fuel nozzle assembly according to an exemplary embodiment of the present disclosure, including a front wall, a rear wall, and a blade extending between the front and rear walls.

[0010] Figure 5 Crossing according to exemplary embodiments of this disclosure Figure 4 The cross-sectional view obtained by cutting section VV.

[0011] Figure 6 Crossing according to exemplary embodiments of this disclosure Figure 4 The cross-sectional view obtained by section VI-VI.

[0012] Figure 7 Crossing according to exemplary embodiments of this disclosure Figure 4 The cross-sectional view taken from section VII-VII.

[0013] Figure 8 This is a cross-sectional view showing alternative profiles of the front and rear walls of a hydrocyclone according to exemplary embodiments of the present disclosure, including a front sloping portion for the front wall.

[0014] Figure 9 This is a cross-sectional view showing an alternative profile of the front and rear walls of the hydrocyclone according to an exemplary embodiment of the present disclosure, including a rearward slope for the rear wall.

[0015] Figure 10 This is a cross-sectional view showing another alternative profile of the front and rear walls of a hydrocyclone according to an exemplary embodiment of the present disclosure, including front and rear inclined portions for the front and rear walls, respectively.

[0016] Figure 11 This is a cross-sectional view showing alternative profiles of the front and rear walls of a hydrocyclone according to exemplary embodiments of the present disclosure, defining a tapering region and a expanding region for the hydrocyclone.

[0017] Figure 12 This is a cross-sectional view of the outlet of a hydrocyclone according to an exemplary embodiment of the present disclosure, such as... Figure 3 A hydrocyclone includes a set of blades having a constant cross-section extending between a front wall and a rear wall.

[0018] Figure 13 This is a cross-sectional view of an alternative cyclone according to an exemplary embodiment of the present disclosure, including a gradually expanding region between the blades extending from the front wall to the outlet at the rear wall.

[0019] Figure 14 This is a cross-sectional view of an alternative outlet for a cyclone separator according to an exemplary embodiment of the present disclosure, including a tapering region between the blades at the outlet extending from front to back.

[0020] Figure 15 This is a cross-sectional view of another alternative outlet for a cyclone separator according to an exemplary embodiment of the present disclosure, including a tapering region for the outlet of the blades extending from the front wall to the rear wall and a subsequent expanding region.

[0021] Figure 16 This is a cross-sectional view of another alternative outlet for a cyclone separator according to an exemplary embodiment of the present disclosure, including a widening region and a subsequent narrowing region for the outlet of the blades extending from the front wall to the rear wall.

[0022] Figure 17This is a cross-sectional view of another fuel nozzle assembly according to an exemplary embodiment of the present disclosure, including a tapered cross-sectional region for the axial passage of the cyclone separator.

[0023] Figure 18 This is a cross-sectional view of yet another fuel nozzle assembly according to an exemplary embodiment of the present disclosure, including a tapered cross-sectional region for the cyclone downstream of both the cyclone impeller and the fuel nozzle. Detailed Implementation

[0024] The aspects disclosed herein relate to fuel nozzle and swirler architectures located within engine components, and more specifically, to fuel nozzle structures configured for use with elevated combustion engine temperatures, such as those using hydrogen fuel and other mixtures. For illustrative purposes, this disclosure is described in connection with a turbine engine of an aircraft having a combustor that drives a turbine. However, it will be understood that the aspects disclosed herein are not limited thereto and can have general applicability in engines as well as in non-aircraft applications, including but not limited to turbojet engines, turboprop engines, turboshaft engines, and turbofan engines, and in non-aircraft applications such as other mobile applications and non-mobile industrial, commercial, and residential applications.

[0025] Reference will now be made in detail to the fuel nozzle assembly architecture, portions thereof, or alternative embodiments thereof, particularly to fuel nozzles and swirlers for supplying fuel to a combustor located within an engine, an example of which is shown as a turbine in the accompanying drawings. Detailed descriptions use numbers and letter reference numerals to denote features in the drawings. Similar or analogous reference numerals in the drawings and description have been used to denote similar or analogous portions of this disclosure.

[0026] The term "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 superior or better than other implementations. Furthermore, unless explicitly stated otherwise, all embodiments described herein should be considered exemplary.

[0027] The terms "front" and "rear" refer to relative positions within an engine or vehicle, and to the normal operating posture of the engine or vehicle. For example, in the context of an engine, "front" refers to the position closer to the engine inlet, and "rear" refers to the position closer to the engine nozzle or exhaust port.

[0028] 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 fluid flow. The terms "forward" or "front" indicate what is in front of something, and "backward" or "rear" indicate what is behind something. For example, when used in relation to fluid flow, forward / front can indicate upstream, and backward / rear can indicate downstream.

[0029] The term “flame sustaining” refers to a state of continuous combustion of fuel such that the flame is sustained along or near the component, and typically along or near a portion of the fuel nozzle and swirler assembly as described herein, and the term “flashback” refers to the retreat of the combustion flame in the upstream direction.

[0030] The term "fluid" can refer to either a gas or a liquid. The term "fluid connectivity" means that fluids can establish connections between specified areas.

[0031] Furthermore, 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 the direction along a ray extending between the engine's central longitudinal axis and the engine's outer perimeter.

[0032] All directional references (e.g., radial, axial, proximal, distal, up, down, upward, downward, left, right, lateral, front, back, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, front, rear, etc.) are for identification purposes only to aid the reader in understanding this disclosure and do not create limitation, particularly regarding the location, orientation, or use of aspects of the disclosure described herein. Connecting references (e.g., attachment, connection, joint, 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 connecting reference does not necessarily mean that two elements are directly connected and fixed relative to each other. Exemplary figures are for illustrative purposes only, and the dimensions, positions, order, and relative sizes reflected in the accompanying figures may vary.

[0033] The singular forms “a,” “an,” and “the” include plural references unless the context clearly indicates otherwise. Furthermore, as used herein, the term “group” or “set” of elements can be any number of elements, including only one.

[0034] As used herein and throughout the specification and claims, approximate language is applied to modify any quantitative representation that may allow for variation without altering its associated essential function. Therefore, values ​​modified by one or more terms such as “about,” “approximately,” “substantially,” and “basically” are not limited to specified precise values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value, or the precision of the method or machine used to construct or manufacture the component and / or system. For example, approximate language may refer to a margin of 1%, 2%, 4%, 5%, 10%, 15%, or 20% of the endpoints of a single value, a range of values, and / or a range of defined values. Scope limitations are combined and interchanged herein and throughout the specification and claims; such scope is identified and includes all subscopes contained herein, unless otherwise indicated by context or language. For example, all scopes disclosed herein include endpoints, and endpoints can be combined independently of each other.

[0035] The burner introduces fuel from the fuel nozzle, mixes it with air through a swirler, and then burns it within the burner to drive the engine. Increased efficiency and reduced emissions have driven the demand for using fuels that burn cleaner and at higher temperatures. There is a need to improve burner durability under these operating parameters, such as improving flame control to prevent the flame from remaining on the fuel nozzle and swirler components.

[0036] Figure 1 This is a schematic diagram of engine 10. As a non-limiting example, engine 10 can be used within an aircraft. Engine 10 may include at least a compressor section 12, a combustion section 14, and a turbine section 16. A drive shaft 18 rotatably connects compressor section 12 and turbine section 16 such that rotation of one affects rotation of the other, and defines a rotation axis 20 for engine 10.

[0037] Compressor section 12 may include a low-pressure (LP) compressor 22 and a high-pressure (HP) compressor 24 fluidly connected in series with each other. Turbine section 16 may include an LP turbine 28 and an HP turbine 26 fluidly connected in series with each other. Drive shaft 18 may operatively connect the LP compressor 22, HP compressor 24, LP turbine 28, and HP turbine 26 together. Alternatively, drive shaft 18 may include an LP drive shaft (not shown) and an HP drive shaft (not shown). The LP drive shaft may connect the LP compressor 22 to the LP turbine 28, and the HP drive shaft may connect the HP compressor 24 to the HP turbine 26. The LP spool may be defined as a combination of the LP compressor 22, LP turbine 28, and LP drive shaft, such that 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, HP turbine 26, and HP drive shaft, such that 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.

[0038] Compressor section 12 may include multiple axially spaced stages. Each stage includes a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary blades. The compressor blades for a stage of compressor section 12 may be mounted to a disc, which is mounted to drive shaft 18. Each set of blades for a given stage may have its own disc. The blades of compressor section 12 may be mounted to a housing that may extend circumferentially around engine 10. It will be understood that the representation of compressor section 12 is merely illustrative and any number of stages may be possible. Furthermore, it is contemplated that any other number of components may be present within compressor section 12.

[0039] Similar to compressor section 12, turbine section 16 may include multiple axially spaced stages, each stage having a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary blades. Blades for a stage of turbine section 16 may be mounted to a disc, which is mounted to drive shaft 18. Each set of blades for a given stage may have its own disc. The blades of the turbine section may be circumferentially mounted to the housing. It should be noted that any number of blades, blades, and stages can be present, as the illustrated turbine section is merely schematic. Furthermore, it is contemplated that any other number of components may be present within turbine section 16.

[0040] Combustion section 14 may be arranged in series between compressor section 12 and turbine section 16. Combustion section 14 may be fluidly coupled to at least a portion of compressor section 12 and turbine section 16, such that combustion section 14 at least partially fluidly couples compressor section 12 to turbine section 16. As a non-limiting example, combustion section 14 may be fluidly coupled to HP compressor 24 at its upstream end and to HP turbine 26 at its downstream end.

[0041] During operation of engine 10, ambient air or atmospheric air is drawn into compressor section 12 via a fan (not shown) upstream of compressor section 12, where it is compressed to define pressurized air. This pressurized air can then flow into combustion section 14, where it mixes with fuel and is ignited to generate combustion gases. HP turbine 26 extracts some work from these combustion gases, driving HP compressor 24. The combustion gases are discharged into LP turbine 28, which extracts additional work to drive LP compressor 22, and the exhaust gas is ultimately discharged from engine 10 via an exhaust section (not shown) downstream of turbine section 16. The drive of LP turbine 28 drives LP spool to rotate the fan (not shown) and LP compressor 22. The pressurized air and combustion gases together define the working airflow through the fan, compressor section 12, combustion section 14, and turbine section 16 of engine 10.

[0042] Figure 2 A fuel nozzle assembly 100 is shown, including a swirler 102 and a fuel nozzle 104 terminating at a nozzle tip 105 and at least partially disposed within the swirler 102. The fuel nozzle 104 includes a fuel passage 112 defining a longitudinal axis 110. The swirler 102 includes a set of blades 106 that impart swirling air as a helical or tangential component to the airflow passing along the blades 106. The swirling air is guided through an exhaust passage 118, and the air is discharged at an outlet 116. The blades 106 include a leading edge (not shown) and a trailing edge 108, and extend between a radially inner wall 120 and a radially outer wall 122, defining the exhaust passage 118 between the radially inner wall 120 and the radially outer wall 122. The trailing edge 108 may be reduced at a reduction angle 114 relative to the longitudinal axis 110 defined through the fuel nozzle 104. In another non-limiting example, the trailing edge reduction angle 114 may be relative to Figure 1 The engine centerline 20. The reduction angle 114 can be between 0 degrees and 90 degrees, or in another non-limiting example, between 30 degrees and 90 degrees, or any other non-zero angle, while other angles or ranges are expected.

[0043] In operation, the airflow can be provided by the swirler 102, which is given a tangential swirling component passing axially around the fuel nozzle 104. The impeller 106 imparts a swirling, tangential, or helical component to the air, causing it to swirl as it exits the swirler 102. The reduction angle 114 for the trailing edge 108 produces a higher angular component to the airflow at the outer diameter of the exhaust passage 118, and a lower angular component relative to the outer diameter at the inner diameter closer to the exhaust passage 118. Additionally, the reduction angle 114 produces a high axial velocity component closer to the inner diameter of the exhaust passage 118, while having a relatively small axial velocity component closer to the outer diameter. The higher swirling component at the outer diameter prevents or reduces flame retention on the fuel nozzle assembly 100, while the higher axial velocity component at the inner diameter prevents flame retention and backfire on the outer surface or end of the fuel nozzle 104. In a non-limiting example, it is contemplated that the impeller 106 or the swirler 102 may be part of the fuel nozzle 104, or integrated with the fuel nozzle 104 as a single component. The reduction angle 114 can begin at any radial blade position relative to the longitudinal axis 110, and it is anticipated that the reduction angle 114 can increase as it extends toward the inner diameter of the cyclone 102, causing the trailing edge 108 to bend. In another example, the reduction angle 114 can begin at any position between 0% and 90% of the channel height between the radial inner wall 120 and the radial outer wall 122, wherein 100% is aligned radially with the radial outer wall 122 and 0% is aligned with the radial inner wall 120.

[0044] Additionally, the nozzle tip 105 can be positioned behind the swirler 102. This rearward positioning provides sufficient space behind the swirler 102 and the fuel nozzle 104 for the wake of the gas flow supplied from the swirler 102 for mixing, which provides for reducing or eliminating flame retention and backfire at the nozzle tip 105.

[0045] The foot 124 of the radial inner wall 120 guides air to slide along the foot 124 and transitions along the outer diameter of the fuel nozzle 104 to significantly reduce the wake at the trailing edge of the radial inner wall 120. The angle on the foot 124 can be defined from 5 degrees to 60 degrees relative to the longitudinal axis 110 or an axis parallel to it to control the flow velocity on the outer diameter of the fuel nozzle 104 and reduce the wake at the trailing edge of the radial inner wall 120. The radial outer wall 122 includes a tapering wall section 126 to guide the flow toward the fuel nozzle 104, thereby generating a high velocity on the outer diameter of the fuel nozzle to prevent flame persistence. The angle of the tapering wall section 126 relative to the longitudinal axis 110 can be between 1 degree and 80 degrees, or between 2 degrees and 80 degrees, while other ranges, such as any non-zero angle, are anticipated. Following the taper of the cyclone passage region defined by the foot 124 and the tapering wall section 126 is a constant region section 128, which forms a well-developed velocity profile at the outlet 116 of the exhaust passage 118, thereby distancing the flame away from the fuel nozzle assembly 100. The length of the constant region section 128 can range from 0.3H to 8.0H, where H is the height of the exhaust passage 118 defined between the radially outer wall 122 located behind the foot 124 and the tapering wall section 126 and the fuel nozzle 104. The tip of the fuel nozzle 104 can be positioned anywhere within the constant region section 128 or the tapering wall section 126 of the cyclone assembly downstream of the cyclone impeller 106.

[0046] Go to Figure 3 Another exemplary fuel nozzle assembly 200 includes a swirler 202 and a fuel nozzle 204. The swirler 202 includes a set of circumferentially arranged radial blades 206 disposed between a front wall 208 and a rear wall 210. The swirler 202 redirects airflow from a radial direction at the radial blades 206 to an axial direction at an axial passage 216 surrounding the fuel nozzle 204. A flared cone 212 extends downstream of the swirler 202 from the axial passage 216. In one example, the flared cone 212 may extend at an angle 218 between -60 degrees (negative 60 degrees) and 80 degrees relative to the longitudinal axis of the fuel nozzle 204, wherein a negative angle defines a tapering cross-sectional region of the flared cone 212, and a positive angle defines a widening cross-sectional region of the flared cone 212, and zero degrees represents a constant cross-section of the flared cone 212. In alternative examples, it is contemplated that the flared cone 212 may include a constant, widening, or tapering cross-sectional region and is not required to be limited to the one shown. In another alternative example, it is expected that the flare will not be included.

[0047] Radial blades 206 can be arranged to introduce radial flow into cyclone separator 202, which discharges at trailing edge 220 at opening 214. Opening 214, sometimes referred to as a nozzle between adjacent radial blades 206, defines an outlet for the nozzle. Opening 214 can be tangentially oriented to impart swirling flow to the airflow supplied from cyclone separator 202. The tangential opening 214, along the outer diameter of the axial passage 216, generates a high-velocity component for the axial airflow, preventing flame retention on the flared cone 212. Additionally, the tangential opening 214 provides a high-velocity component along the inner diameter of the axial passage 216, preventing flame retention or backfire at fuel nozzle 204.

[0048] Turning Figure 4 A swirler 300 for a fuel nozzle assembly (such as the fuel nozzle assembly described herein) includes a housing 302 having a front wall 304 and a rear wall 306. A set of blades 308 extends between the front wall 304 and the rear wall 306 for imparting tangential swirling flow to the airflow supplied to the fuel nozzle assembly.

[0049] Go to Figure 5 ,along Figure 4 The section VV is cut close to the front wall 304, showing the radially arranged blades 308 relative to the annular front wall 304. Figure 6 Showing along Figure 4 The cross-sectional view taken at section VI-VI shows the sections located at the front wall 304 and the rear wall 306 (see section VI-VI). Figure 4 306 on the rear wall Figure 5-7 The blades 308 (not shown in the image) are shown to be rotating from the radial direction to the tangential direction, wherein the trailing edge 310 of each blade 308 is tangentially rotated. Figure 7 Showing along Figure 4 The cross-sectional view taken at section VII-VII shows the section near the rear wall 306, showing the trailing edge 310 of the blade 308 further tangentially turning, while extending less tangentially toward the leading edge 312 compared to the trailing edge 310. The blade 308, radially shown in section VV, is arranged along a radius extending from the center of the hydrocyclone before turning radially. Figure 6 and 7 As shown. The axial position at which the impeller 308 begins to turn from radial to axial can vary between 0% and 80% of the total impeller height, wherein the impeller height is defined between the front wall 304 and the rear wall 306 of the hydrocyclone 300.

[0050] As the impeller 308 rotates tangentially along its trailing edge 310, the airflow guided along the impeller 308 provides a peak airflow velocity before interacting with the fuel flow supplied by the fuel nozzle. The tangential profile of the trailing edge 310 can provide a high tangential velocity component along the outer diameter of the axial swirler channel downstream of the swirler 300, which prevents flame hold-up on the fuel nozzle assembly or the downstream flare cone. Figure 5 The forward radial component of the blade 308, defined by the geometry shown in section VV, does not have a tangential component of the flow velocity, and generates a high axial velocity when the flow turns toward the fuel nozzle. This high axial velocity generated by the forward radial component of the blade 308 results in a high axial velocity at the rear end of the fuel nozzle, preventing flame retention at the tip of the fuel nozzle.

[0051] Figure 4 The front wall 304 and the rear wall 306 are shown, which are aligned parallel to each other, or orthogonal to the longitudinal axis of the fuel nozzle, or both. Figure 8-11 Non-limiting alternative examples are shown that can be used to change the velocity profile of the airflow provided by the cyclone. Figure 8 A front wall 400 is shown, which includes an inclination that can be defined by an inclination angle 402, defined relative to a rear wall 404 or a radius 408 extending from the longitudinal axis of the fuel nozzle and swirler assembly. Alternatively, the front wall 400 can be defined to be non-orthogonal to the longitudinal extent of the fuel nozzle used with a swirler including the front wall 400. Similarly, Figure 9 The rear wall 414 is shown, which includes an inclination defined by an inclination angle 412 relative to the radius 418 or the front wall 410. Figure 8 The forward or backward tilt of the cyclone separator 406, 416 can define the tapered cross-sectional region 406, 416, which can provide increased velocity to the airflow passing through the cyclone separator. Based on the angle or tilt of the wall, the location where the local velocity profile can be increased or decreased can be controlled, which can improve the airflow velocity profile and reduce or prevent flame persistence at the fuel nozzle assembly. When the passage between the front wall 410 and the rear wall 414 changes, the blade span in the cyclone separator located between the front wall 410 and the rear wall 414 can be reduced in the rearward direction, which helps to achieve the desired velocity profile as the airflow exits the blades. The tilt angles 402, 412 can be between 0 degrees and 45 degrees, while other ranges are anticipated.

[0052] In another example, Figure 10The diagram shows a front wall 420 and a rear wall 424, both of which, in a non-limiting example, are inclined at an angle 422 relative to the longitudinal extent of the fuel nozzle or engine centerline, deviating from an orthogonal orientation. The inclined front wall 420 and rear wall 424 also provide a tapered cross-sectional area 426, thereby providing an increased velocity to the airflow supplied by the vortex. For example, the angle 422 can range from 0 degrees to 45 degrees.

[0053] Figure 11 Another example is shown, including a front wall 430 and a rear wall 434, both of which taper to define a reduced cross-sectional area 432, transitioning to a widening portion of the front and rear walls 430 and 434, defining a widening cross-sectional area 436. Instead of flat surfaces, the front and rear walls 430 and 434 may be curved. For example, the radial height of the channel where the transition between the taper and widening regions occurs may be between 20% and 80% of the total radial height of the hydrocyclone channel.

[0054] It should be understood that other combinations exist in which the front or rear wall includes an incline or sloping shape, or the curvature of the wall, concave or convex, which, respectively, define an enlarged or reduced cross-sectional area, or any combination thereof, independent of or complementary to the other wall. It should be understood that the front and rear walls of the cyclone separator can be angled, separately, together, or complementaryly. Furthermore, each wall can be angled, non-angled, or discretely curved to define a tapering or expanding portion of the cyclone separator, which can define a complex airflow profile.

[0055] Figure 12 An enlarged cross-sectional view of a portion of an exemplary cyclone separator 500 is shown. The cyclone separator 500 includes two blades 502 extending between a front wall 504 and a rear wall 506. Each blade 502 may include a constant cross-sectional area extending between the front wall 504 and the rear wall 506.

[0056] Figure 13-16 An alternative example of the cross-sectional profile of a hydrocyclone with blades defined between the front and rear walls is shown. Figure 13 A cyclone separator 510 is shown with blades 512, each blade comprising an enlarged cross-sectional flow region 518 extending in a direction from the front wall 514 to the rear wall 516, or a reduced blade thickness extending from the front wall 514 to the rear wall 516. This geometry produces a lower flow region at the front wall 514 of the blade passage and a relatively higher flow region at the rear wall 516 of the blade passage, resulting in high velocities across the outer diameter of the axial cyclone separator passage, such as in… Figure 3As described, the relatively low velocity in the axial swirler channel on the outer diameter of the fuel nozzle. In other words, the geometry produces a peak velocity profile at the radially outer part of the axial swirler channel. The high-speed flow on the outer diameter of the swirler or flare cone prevents flame retention on the flare cone.

[0057] Figure 14 A cyclone separator 520 with blades 522 is shown, the blades 522 comprising a reduced cross-sectional flow region 528 or an increased blade thickness extending from a front wall 524 to a rear wall 526. This geometry produces a peak radial inward velocity profile at the axial cyclone separator passage. The high-speed component on the outer diameter of the fuel nozzle reduces or eliminates flame retention at the fuel nozzle.

[0058] Figure 15 The cyclone separator 530 includes blades 532, which comprise a profile including a decreasing cross-sectional flow region 538 extending between a front wall 534 and a rear wall 536, followed by an increasing cross-sectional flow region 539, or an increasing blade thickness extending between the front wall 534 and the rear wall 536, transitioning to a decreasing blade thickness. This geometry produces a bi-peak velocity profile, where the peak velocity occurs on both the inner and outer diameters of the cyclone separator's axial passage. This generates high-speed flow near the flared cone and the fuel nozzle wall, preventing flame persistence on both surfaces.

[0059] Figure 16 The cyclone separator 540 includes blades 542, which comprise an enlarged cross-sectional flow region 548 extending from a front wall 544 to a rear wall 546, transitioning to a reduced cross-sectional flow region 550, or include an enlarged blade thickness extending from the front wall 544 to the rear wall 546, transitioning to a reduced blade thickness. This geometry creates a central peak velocity profile in the axial passage of the cyclone separator, preventing flame hold-up or backfire at the center of the axial passage. The transition in blade thickness can occur at any location from 20% to 80% of the length defined by the front wall 544 to the rear wall 546 of the radial cyclone passage. It is possible that the blade surface can be a curved surface instead of a flat surface, or a combination thereof is possible. The reduced or tapered cross-sectional region can be used to accelerate the flow, while the enlarged or tapered cross-sectional region can be used to decelerate the flow, which can be directed towards the inner or outer diameter of the axial passage of the cyclone separator to reduce the occurrence of flame hold-up on the fuel nozzle assembly. Furthermore, although the cross-sectional view is shown closer to the outlet arrangement of the cyclone assembly, it should be understood that the cross-section can be defined at any location between the leading and trailing edges of a particular blade, and it is further anticipated that such cross-sectional variation can occur in the direction extending from the leading edge to the trailing edge, which is opposite to or complementary to the variation extending between the front wall 544 and the rear wall 546.

[0060] The variable profile of the impeller extending between the front and rear walls can provide different velocity profiles defining the swirling air exiting the swirler. The variable velocity profile can be used to prevent flame holding at points on the fuel nozzle assembly, and this profile can be used to create complex flow profiles to prevent flame holding. Furthermore, different velocity profiles can be used to control fuel and air mixing in the fuel nozzle assembly and in the primary zone of the downstream burner.

[0061] In another example, it is expected that the blades (such as...) Figure 12-16 The impeller shown may include a cross-section that varies in a radial direction orthogonal to the direction extending between the front and rear walls. Thus, similar to that disclosed in the axial direction, the impeller may taper, expand, remain constant, or any combination thereof in the radial direction. Furthermore, it is contemplated that the impeller may include a varying cross-section in both the radial and axial directions. For example, the impeller may taper from the front to the rear wall in the axial direction, while the same impeller may expand in a radial direction orthogonal to the axial direction. Thus, it should be understood that the impeller profile can be used to determine or define a velocity profile that can be tailored to a fuel nozzle assembly or a specific fuel type, which can be used to reduce or eliminate flame retention or backfire, and to mix fuel and air to increase efficiency.

[0062] Figure 17 A fuel nozzle assembly 600 is shown with a swirler 602 surrounding a fuel nozzle 604. The swirler 602 includes an axial passage 606 discharging around the fuel nozzle 604. The axial passage 606 may include a tapered portion 608. The axial passage 606 may be spaced apart from the fuel nozzle 604 by a swirler wall 610. The swirler wall 610 may include an angled portion 612 defining the tapered portion 608. The tapered portion 608 provides an increased velocity of the swirler air discharging from the axial passage 606, which prevents flame retention on the fuel nozzle assembly 600. A throat 614 is defined in an accelerated flow passage downstream of the fuel nozzle 604 and upstream of the flared cone 616 to prevent flame backfire on the fuel nozzle 604. The position of the throat 614 relative to the fuel nozzle 604 can be from 0D to 30D, where D is the diameter of the fuel orifice 618 at the end of the fuel nozzle 604, and in one example, D may be the diameter of the smallest fuel orifice.

[0063] A protrusion 620 may be formed in the cyclone separator 602. The protrusion may be circular or linear, or a combination thereof, while any suitable shape is contemplated. The protrusion 620 defines a tapering cross-section downstream of the angled portion 612, which defines the throat 614 as the smallest cross-sectional area of ​​the fuel nozzle assembly 600 downstream of the fuel nozzle 604 and upstream of the flared cone 616. The protrusion 620 may be positioned between 0D and 30D downstream of the fuel nozzle 604, where D is the diameter of the fuel orifice 618, and here 0D is aligned with the end of the fuel nozzle.

[0064] Figure 18 A fuel nozzle assembly 700 includes a cyclone separator 702 surrounding a fuel nozzle 704. The cyclone separator 702 includes an axial channel 706, which includes a tapered portion 708 defining a tapered section surrounding the fuel nozzle 704. The cyclone separator 702 includes a downstream housing portion 716 extending rearward of the fuel nozzle 704, defining a truncated nozzle 710 that encloses a mixture of air from the cyclone separator 702 and fuel from the fuel nozzle 704. The truncated nozzle 710 provides additional space between the truncated nozzle 710 and an outer flared cone 712, which provides space for an acoustic damper 714. The tapered cross-sectional area defined by the truncated nozzle 710 accelerates the flow of fuel and air discharged from the fuel nozzle 704 and swirler 702 to prevent flame sustaining or backfire. Simultaneously, the damper 714 can be used to reduce vibrations generated by the fuel nozzle assembly 200, providing further flame control to prevent flame sustaining or backfire. Thus, the damper 714 can be an acoustic damper that dampens engine-generated noise for quieter operation, and utilizes the flared cone 712 and damper 714 to reduce or absorb vibrational energy. For the different fuel nozzle assemblies 700 arranged annularly around the combustor, the damper volumes can be the same or different to address a wider range of combustion dynamic frequencies. It is possible that volume partitions exist within each individual damper volume placed around the swirler 702, where discrete volumes can be tuned to specific frequencies. The damper 714 can extend into the combustion chamber above the flared cone 712.

[0065] It should be understood that the flare can be made to expand gradually, remain constant, or contract gradually in the flow direction. This can prevent flame retention or backfire, and allow the fuel-air mixture to expand, which can improve efficiency and reduce emissions. In another example, no flare is expected.

[0066] It should be understood that fuels with higher combustion temperatures and rates, or lighter weights, compared to air or other fuels, can provide reduced or eliminated emissions, or improved efficiency, without increasing emissions. In one example, hydrogen fuel or hydrogen-based fuels could be used, which could eliminate carbon emissions without negatively impacting efficiency. Such fuels, including hydrogen, require better flame control to prevent flame hold-up or backfire on the burner hardware. The aspects described herein can increase burner durability that current burners may not provide when using such fuels.

[0067] As will be understood from the description herein, aspects may be interchanged or combined, and this disclosure is not limited to the embodiments described herein. Those skilled in the art will recognize that the aspects described herein may be interchanged, combined, added, or otherwise combined to form additional embodiments.

[0068] This written description uses examples to disclose this disclosure, including best practices, and also enables any person skilled in the art to practice this disclosure, including making and using any apparatus or system and performing any incorporated methods. The patentable scope of this disclosure is defined by the claims, but may include other examples that would occur to a person skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

[0069] 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 arranged in a tandem flow configuration, the combustor section including a fuel nozzle assembly comprising: a fuel nozzle defining a fuel passage defining a longitudinal axis; and a swirler surrounding the fuel nozzle, the swirler having blades disposed within the swirler configured to impart a tangential component to an air supply provided through the swirler, the blades including a leading edge and a trailing edge; wherein the trailing edge is arranged at a reduction angle relative to the longitudinal axis.

[0070] The turbine engine according to any one of the foregoing clauses, wherein the vortex further includes a radial inner wall and a radial outer wall defining an exhaust passage.

[0071] The turbine engine according to any one of the foregoing clauses, wherein the radial inner wall includes a foot.

[0072] The turbine engine according to any one of the foregoing clauses, wherein the radial outer wall includes a tapering section.

[0073] The turbine engine according to any one of the foregoing clauses, wherein the tapering section is at least partially aligned with the foot in a direction orthogonal to the longitudinal axis.

[0074] The turbine engine according to any one of the foregoing clauses, wherein the reduction angle is less than 90 degrees and is non-zero.

[0075] The turbine engine according to any one of the foregoing clauses, wherein the fuel nozzle terminates behind the cyclone.

[0076] A fuel nozzle and swirler assembly for an engine, the fuel nozzle and swirler assembly comprising: a fuel nozzle including a fuel passage defining a longitudinal axis; and a swirler surrounding the fuel nozzle, the swirler including: a front wall, a rear wall, and a set of blades, the rear wall being spaced apart from the front wall to define a swirler passage therebetween, the set of blades being disposed in the swirler passage and extending between the front wall and the rear wall, the set of blades being configured to impart a tangential component to a quantity of fluid passing through the swirler, wherein each blade in the set of blades is oriented from a radial orientation at the front wall to a tangential orientation at the rear wall.

[0077] The fuel nozzle and cyclone assembly according to any one of the foregoing clauses, wherein the front wall is arranged at an angle, the angle being deviated from an axis defined as orthogonal to the longitudinal axis.

[0078] The fuel nozzle and swirler assembly according to any one of the foregoing clauses, wherein the radial orientation is defined in a radial direction orthogonal to the longitudinal axis.

[0079] The fuel nozzle and swirler assembly according to any one of the foregoing clauses, wherein the tangential orientation is in a direction tangential to the radial direction.

[0080] A fuel nozzle and swirler assembly for an engine, the fuel nozzle and swirler assembly comprising: a fuel nozzle including a fuel passage defining a longitudinal axis; and a swirler surrounding the fuel nozzle, the swirler including: a front wall, a rear wall, and a set of blades, the rear wall being spaced apart from the front wall to define a swirler passage therebetween, the set of blades being disposed in the swirler passage and extending between the front wall and the rear wall, each blade in the set of blades including a trailing edge, the set of blades being used to impart a tangential component to a certain amount of fluid passing through the swirler; wherein the trailing edge is arranged at a reduction angle relative to the longitudinal axis.

[0081] The fuel nozzle and cyclone assembly according to any one of the foregoing clauses, wherein one of the front wall and the rear wall is arranged at an angle, wherein the angle is defined relative to a radius extending orthogonally to the longitudinal axis.

[0082] The fuel nozzle and swirler assembly according to any one of the foregoing clauses, wherein the tilt angle defines a tapering cross-sectional area in the flow direction through the swirler.

[0083] The fuel nozzle and swirler assembly according to any one of the foregoing clauses further includes a widening cross-section region downstream of the contracting cross-section region relative to the flow direction through the swirler.

[0084] The fuel nozzle and swirler assembly according to any one of the foregoing clauses further includes a gradually expanding cross-section region upstream of the tapering cross-section region in the flow direction.

[0085] A fuel nozzle and swirler assembly for an engine, the fuel nozzle and swirler assembly comprising: a fuel nozzle including a fuel passage defining a longitudinal axis; a swirler surrounding the fuel nozzle and including a front wall and a rear wall spaced apart from the front wall to define a swirler passage therebetween; and a set of blades disposed in the swirler passage and extending between the front wall and the rear wall, each blade in the set of blades extending between a leading edge and a trailing edge; wherein the trailing edge of each blade in the set of blades is arranged at a reduced angle relative to the longitudinal axis.

[0086] The fuel nozzle and cyclone assembly according to any one of the foregoing clauses, wherein the set of blades defines at least one of an enlarged cross-sectional flow region or a reduced cross-sectional flow region.

[0087] The fuel nozzle and cyclone assembly according to any one of the foregoing clauses, wherein the set of blades includes the increased cross-sectional flow region or the decreased cross-sectional flow region in a direction extending from the front wall to the rear wall.

[0088] The fuel nozzle and cyclone assembly according to any one of the foregoing clauses, wherein the set of blades includes the increased cross-sectional flow region or the decreased cross-sectional region in a radial direction, the radial direction being orthogonal to the direction extending from the front wall to the rear wall.

[0089] The fuel nozzle and cyclone assembly according to any one of the foregoing clauses, wherein the set of blades defines both the increased cross-sectional flow region and the decreased cross-sectional flow region.

[0090] The fuel nozzle and swirler assembly according to any one of the foregoing clauses, wherein the increased cross-sectional flow region is disposed adjacent to the front wall and the decreased cross-sectional flow region is disposed adjacent to the rear wall.

[0091] The fuel nozzle and cyclone assembly according to any one of the foregoing clauses, wherein the cyclone further includes a tapered portion disposed downstream of the set of blades.

[0092] The fuel nozzle and cyclone assembly according to any one of the foregoing clauses further includes a protrusion disposed downstream of the tapered portion.

[0093] The fuel nozzle and cyclone assembly according to any one of the foregoing clauses further includes a damper disposed radially outside the tapering portion.

[0094] A fuel nozzle and swirler assembly for an engine, the fuel nozzle and swirler assembly comprising: a fuel nozzle including a fuel passage defining a longitudinal axis; a swirler surrounding the fuel nozzle and including a front wall and a rear wall spaced apart from the front wall to define a swirler passage therebetween; and a set of blades disposed in the swirler passage and extending between the front wall and the rear wall, each blade of the set of blades extending between a leading edge and a trailing edge; wherein the set of blades defines at least one of an enlarged cross-sectional flow region or a reduced cross-sectional flow region.

[0095] The fuel nozzle and cyclone assembly according to any one of the foregoing clauses, wherein the set of blades includes the increased cross-sectional flow region or the decreased cross-sectional flow region in a direction extending from the front wall to the rear wall.

[0096] The fuel nozzle and cyclone assembly according to any one of the foregoing clauses, wherein the set of blades includes the increased cross-sectional flow region or the decreased cross-sectional region in a radial direction, the radial direction being orthogonal to the direction extending from the front wall to the rear wall.

[0097] The fuel nozzle and cyclone assembly according to any one of the foregoing clauses, wherein the set of blades defines both the increased cross-sectional flow region and the decreased cross-sectional flow region.

[0098] The fuel nozzle and swirler assembly according to any one of the foregoing clauses, wherein the increased cross-sectional flow region is disposed adjacent to the front wall and the decreased cross-sectional flow region is disposed adjacent to the rear wall.

[0099] The fuel nozzle and cyclone assembly according to any one of the foregoing clauses, wherein the cyclone further includes a tapered portion disposed downstream of the set of blades.

[0100] The fuel nozzle and cyclone assembly according to any one of the foregoing clauses further includes a protrusion disposed downstream of the tapered portion.

[0101] The fuel nozzle and cyclone assembly according to any one of the foregoing clauses further includes a damper disposed radially outside the tapering portion.

[0102] A fuel nozzle and swirler assembly for an engine, the fuel nozzle and swirler assembly comprising: a fuel nozzle including a fuel passage defining a longitudinal axis; and a swirler surrounding the fuel nozzle, the swirler including: a front wall, a rear wall, and a set of blades, the rear wall being spaced apart from the front wall to define a swirler passage therebetween, the set of blades being disposed in the swirler passage and extending between the front wall and the rear wall for imparting a tangential component to a certain amount of fluid passing through the swirler; wherein at least one of the front wall and the rear wall is arranged at an angle relative to a radius defined orthogonal to the longitudinal axis.

[0103] The fuel nozzle and cyclone assembly according to any one of the foregoing clauses, wherein both the front wall and the rear wall are arranged at the aforementioned angle.

[0104] The fuel nozzle and swirler assembly according to any one of the foregoing clauses, wherein the tilt angle defines a tapering cross-sectional area in the flow direction through the swirler.

[0105] The fuel nozzle and swirler assembly according to any one of the foregoing clauses further includes a widening cross-section region downstream of the contracting cross-section region relative to the flow direction through the swirler.

[0106] The fuel nozzle and swirler assembly according to any one of the foregoing clauses further includes a gradually expanding cross-section region upstream of the tapering cross-section region in the flow direction.

Claims

1. A fuel nozzle and swirler assembly for an engine, characterized in that, The fuel nozzle and cyclone assembly includes: A fuel nozzle, the fuel nozzle including a fuel passage defining a longitudinal axis; and A cyclone separator surrounding the fuel nozzle, the cyclone separator comprising: Front wall, The rear wall, spaced apart from the front wall, defines a cyclone channel therebetween. A set of blades, disposed within the hydrocyclone channel and extending between the front and rear walls, is configured to impart a tangential component to a given amount of fluid passing through the hydrocyclone. Each of the set of blades rotates from a radial orientation at the front wall to a tangential orientation at the rear wall; and A flared cone that extends from the hydrocyclone and is arranged at an angle relative to the longitudinal axis.

2. The fuel nozzle and cyclone assembly according to claim 1, characterized in that, The front wall is arranged at an angle, the angle of which deviates from an axis defined as orthogonal to the longitudinal axis.

3. The fuel nozzle and cyclone assembly according to claim 1, characterized in that, The radial orientation is defined in a radial direction orthogonal to the longitudinal axis.

4. The fuel nozzle and cyclone assembly according to claim 3, characterized in that, The tangential orientation is in a direction tangential to the radial direction.

5. A fuel nozzle and swirler assembly for an engine, characterized in that, The fuel nozzle and cyclone assembly includes: A fuel nozzle, the fuel nozzle including a fuel passage defining a longitudinal axis; and A cyclone separator surrounding the fuel nozzle, the cyclone separator comprising: Front wall, The rear wall, spaced apart from the front wall, defines a cyclone channel therebetween. A set of blades, which are disposed in the hydrocyclone channel and extend between the front wall and the rear wall, are used to impart a tangential component to a certain amount of fluid passing through the hydrocyclone; At least one of the front wall and the rear wall is arranged at an angle relative to a radius defined orthogonal to the longitudinal axis; and A flared cone that extends from the hydrocyclone and is arranged at an angle relative to the longitudinal axis; The cyclone separator is externally connected to the fuel nozzle.

6. The fuel nozzle and cyclone assembly according to claim 5, characterized in that, The front wall and the rear wall are both arranged at the aforementioned angle.

7. The fuel nozzle and cyclone assembly according to claim 5, characterized in that, The tilt angle defines a tapering cross-sectional region in the flow direction through the cyclone separator.

8. The fuel nozzle and cyclone assembly according to claim 7, characterized in that, It further includes a gradually expanding cross-section region downstream of the contracting cross-section region relative to the flow direction through the cyclone.

9. The fuel nozzle and cyclone assembly according to claim 7, characterized in that, It further includes a gradually expanding cross-sectional region upstream of the contracting cross-sectional region in the flow direction.

10. A fuel nozzle and swirler assembly for an engine, characterized in that, The fuel nozzle and cyclone assembly includes: A fuel nozzle, the fuel nozzle including a fuel passage defining a longitudinal axis; A cyclone surrounding the fuel nozzle and including a front wall and a rear wall spaced apart from the front wall to define a cyclone passage therebetween; and A set of blades, the set of blades being disposed in the hydrocyclone channel and extending between the front wall and the rear wall, each blade in the set of blades extending between a leading edge and a trailing edge; The set of blades defines at least one of an enlarged cross-sectional flow region or a reduced cross-sectional flow region; Each of the set of blades rotates from a radial orientation at the front wall to a tangential orientation at the rear wall; and A flared cone that extends from the hydrocyclone and is arranged at an angle relative to the longitudinal axis.

11. The fuel nozzle and cyclone assembly according to claim 10, characterized in that, The set of blades includes either the increased cross-sectional flow region or the decreased cross-sectional flow region in the direction extending from the front wall to the rear wall.

12. The fuel nozzle and cyclone assembly according to claim 10, characterized in that, The set of blades includes either the increased cross-sectional flow region or the decreased cross-sectional flow region in the radial direction, the radial direction being orthogonal to the direction extending from the front wall to the rear wall.

13. The fuel nozzle and cyclone assembly according to claim 10, characterized in that, The set of blades defines both the increased cross-sectional flow region and the decreased cross-sectional flow region.

14. The fuel nozzle and cyclone assembly according to claim 13, characterized in that, The increased cross-sectional flow region is located adjacent to the front wall, and the decreased cross-sectional flow region is located adjacent to the rear wall.

15. The fuel nozzle and cyclone assembly according to claim 10, characterized in that, The cyclone further includes a tapered section arranged downstream of the set of blades.

16. The fuel nozzle and cyclone assembly according to claim 15, characterized in that, It further includes a protrusion located downstream of the tapered portion.

17. The fuel nozzle and cyclone assembly according to claim 15, characterized in that, It further includes a damper arranged radially outside the tapering portion.

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