Fuel nozzles and swirlers

Abstract

A turbine engine may include a compressor section, a combustion section, and a turbine section in a serial flow arrangement. The combustion section may include a combustor liner, a dome assembly coupled to the combustor liner, a fuel nozzle fluidly coupled to the dome assembly, a combustion chamber fluidly coupled to the fuel nozzle, and at least one set of dilution openings located in the dome assembly or the combustor liner and fluidly coupled to the combustion chamber. A swirler may define at least one passage extending between at least one annular inlet and at least one annular outlet, wherein the at least one annular inlet is fluidly coupled to the compressor section. The variable area device may be movable relative to at least a portion of the at least one set of dilution openings or the swirler.

Description

[0001] CROSS-REFERENCE TO RELATED APPLICATIONS

[0002] This application claims priority to U.S. Provisional Application Serial No. 63 / 298,784, filed on January 12, 2022, and U.S. Patent Application Serial No. 17 / 686,904, filed on March 4, 2022, the contents of which are incorporated herein by reference. Technical Field

[0003] The present subject matter generally relates to a combustor for a turbine engine having one or both of a fuel nozzle and a swirler. Background Art

[0004] An engine, such as a turbine engine, may include a turbine or other features driven by the combustion of a combustible fuel within the engine's combustor. The engine utilizes a fuel nozzle to inject the combustible fuel into the combustor. A swirler provides mixing of the fuel and air for efficient combustion. BRIEF DESCRIPTION OF THE DRAWINGS

[0005] In the description with reference to the accompanying drawings, a full and enabling disclosure of the present disclosure, including the best mode thereof, is set forth to one of ordinary skill in the art, wherein:

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

[0007] Figure 2 is a method for implementing an exemplary embodiment of the present disclosure Figure 1 Schematic cross-sectional view of a burner of an engine.

[0008] Figure 3 is a cross-sectional view of a fuel nozzle assembly according to an exemplary embodiment of the present disclosure.

[0009] Figure 4 According to an exemplary embodiment of the present disclosure Figure 3 Variations of the fuel nozzle assembly.

[0010] Figure 5 is an excerpt from an exemplary embodiment of the present disclosure. Figure 4 Cross-sectional view of cross section VV.

[0011] Figure 6 According to an exemplary embodiment of the present disclosure Figure 3 Another variation of a fuel nozzle assembly.

[0012] Figure 7 is an excerpt from an exemplary embodiment of the present disclosure. Figure 6 Cross-sectional view of cross section VII-VII.

[0013] Figure 8 is a method for implementing an exemplary embodiment of the present disclosure Figure 3 、 Figure 4 or Figure 6 Cross-sectional view of an actuator of a fuel nozzle assembly.

[0014] Figures 9A-9B According to an exemplary embodiment of the present disclosure Figure 8 A variant of the actuator.

[0015] Figure 10 According to an exemplary embodiment of the present disclosure Figure 2 burner variants.

[0016] Figure 11 According to an exemplary embodiment of the present disclosure Figure 2 Another variant of the burner.

[0017] Figure 12 is an excerpt from an exemplary embodiment of the present disclosure. Figure 11 Cross-sectional view of cross section XII-XII. DETAILED DESCRIPTION

[0018] Aspects disclosed herein are directed to fuel nozzles and swirler structures located within engine components, and more specifically, to fuel nozzle structures, nozzle cover structures, or swirler structures configured for use with elevated combustion engine temperatures, such as those using hydrogen fuel or hydrogen fuel mixtures. Higher temperature fuels can eliminate carbon emissions, but due to the higher flame speeds and high temperatures, challenges associated with flame holding or flashback are generated. Current combustors include durability risks due to flame holding or flashback on combustor components when using such high temperature fuels. For purposes of illustration, the present disclosure will be described with respect to a turbine engine for an aircraft having a combustor that drives a turbine. However, it will be understood that the aspects disclosed herein are not limited thereto.

[0019] During combustion, engines generate high local temperatures. Efficiency and carbon emission requirements require fuels that burn hotter than conventional fuels, or reduced carbon emissions require the use of fuels with higher combustion temperatures, such as hydrogen. For example, combustion temperatures and velocities may be higher than those of current engine fuels, so existing engine designs will face durability risks from operating at the elevated temperatures required to meet rising efficiency and emissions standards.

[0020] Reference will now be made in detail to the fuel nozzle and swirler architecture, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and the description have been used to refer to like or similar parts of the present disclosure.

[0021] 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, all embodiments described herein are to be considered exemplary unless expressly stated otherwise.

[0022] The terms "fore" 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, the front position refers to the position closer to the engine inlet, while the aft position refers to the position closer to the engine nozzle or exhaust.

[0023] 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 in the same direction as the direction of fluid flow. The terms "forward" or "front" mean in front of something, and "rearward" or "rear" mean behind something. For example, when used in relation to fluid flow, forward / front can refer to upstream, and rearward / rear can refer to downstream.

[0024] The term "fluid" may be a gas or a liquid. The term "fluid communication" means that a fluid is able to establish a connection between designated areas.

[0025] The term "flame holding" refers to a condition in which the combustion of fuel continues such that a flame is maintained along or near a component, and typically along or near a portion of a fuel nozzle assembly as described herein, and "flashback" refers to the retreat of the combustion flame in an upstream direction. The term "flame scrubbing" refers to a condition in which the combustion flame scrubs against an inner or outer combustor liner, or other component.

[0026] Furthermore, as used herein, the term "radial" or "radially" refers to directions away from a common center. For example, in the overall context of a turbine engine, radial refers to directions along a ray extending between the central longitudinal axis of the engine and the periphery of the engine.

[0027] All directional references (e.g., radial, axial, front, rear, clockwise, counterclockwise, upstream, downstream, forward, rearward, etc.) are for identification purposes only to help the reader understand the present disclosure and do not impose limitations, particularly with respect to the position, orientation, or use of the disclosed aspects described herein. Connection references (e.g., attach, couple, and connect) are to be interpreted broadly and may include intermediate structural elements between sets of elements and relative movement between elements, unless otherwise indicated. Therefore, a connection reference does not necessarily mean that two elements are directly connected and fixed relative to each other. The exemplary figures are for illustration purposes only, and the dimensions, positions, orders, and relative sizes reflected in the accompanying figures may vary.

[0028] The singular forms "a," "an," and "the" include plural references unless the context clearly dictates otherwise. Also, as used herein, the term "set" or "a group of" elements may refer to any number of elements, including only one.

[0029] As used herein throughout the specification and claims, approximating language is applied to modify any quantitative expression that can be allowed to vary without causing a change in its associated basic function. Therefore, values ​​modified by one or more terms such as "approximately" and "substantially" are not limited to the specified exact values. In at least some cases, approximate language can correspond to the accuracy of an instrument used to measure a value, or the accuracy of a method or machine used to construct or manufacture a component and / or system. In at least some cases, approximate language can correspond to the accuracy of an instrument used to measure a value, or the accuracy of a method or machine used to construct or manufacture a component and / or system. For example, approximate language can refer to a margin of 1%, 2%, 4%, 5%, 10%, 15% or 20% of an endpoint of a single value, a range of values ​​and / or a range of values. Here and throughout the specification and claims, range limitations are combined and interchanged, and such ranges are identified and include all subranges contained therein unless the context or language indicates otherwise. For example, all ranges disclosed herein include endpoints, and the endpoints can be combined independently of each other.

[0030] The combustor introduces fuel from the fuel nozzle, mixes with air provided by the swirler, and then burns within the combustor to drive the engine. Increased efficiency and reduced emissions have driven the use of fuels that burn cleaner or at higher temperatures. There is a need to improve the durability of the combustor under these operating parameters, such as improving flame control to prevent flame stagnation on the fuel nozzle and swirler components.

[0031] Figure 11 is a schematic diagram of an exemplary turbine engine 10. As a non-limiting example, the turbine engine 10 may be used within an aircraft. The turbine engine 10 may include at least a compressor section 12, a combustion section 14, and a turbine section 16. A drive shaft 18 rotationally couples the compressor section 12 and the turbine section 16 so that rotation of one affects rotation of the other and defines an axis of rotation 20 of the turbine engine 10.

[0032] The compressor section 12 may include a low-pressure (LP) compressor 22 and a high-pressure (HP) compressor 24 fluidly coupled in series with each other. The turbine section 16 may include an HP turbine 26 and an LP turbine 28 fluidly coupled in series with each other. The drive shaft 18 may operably couple the LP compressor 22, the HP compressor 24, the HP turbine 26, and the LP turbine 28 together. Alternatively, the drive shaft 18 may include an LP drive shaft (not shown) and an HP drive shaft (not shown). The LP drive shaft may couple the LP compressor 22 to the LP turbine 28, and the HP drive shaft may couple the HP compressor 24 to the HP turbine 26. The LP spool may be defined as the combination of the LP compressor 22, the LP turbine 28, and the LP drive shaft, such that rotation of the LP turbine 28 may apply driving force to the LP drive shaft, which in turn may rotate the LP compressor 22. The HP spool may be defined as the combination of the HP compressor 24, the HP turbine 26, and the HP drive shaft, such that rotation of the HP turbine 26 may apply driving force to the HP drive shaft, which in turn may rotate the HP compressor 24.

[0033] The compressor section 12 may include a plurality of axially spaced stages. Each stage includes a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary vanes. The compressor blades for a stage of the compressor section 12 may be mounted to a disk, which is mounted to the drive shaft 18. Each set of blades for a given stage may have its own disk. The vanes of the compressor section 12 may be mounted to a casing, which may extend circumferentially around the turbine engine 10. It should be understood that the representation of the compressor section 12 is merely schematic and that there may be any number of stages. Further, it is contemplated that there may be any other number of components within the compressor section 12.

[0034] Similar to the compressor section 12, the turbine section 16 may include a plurality of axially spaced stages, with each stage having a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary vanes. The turbine blades for a stage of the turbine section 16 may be mounted to disks, which are mounted to the drive shaft 18. Each set of blades for a given stage may have its own disk. The vanes of the turbine section may be mounted to the casing in a circumferential manner. It should be noted that there may 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 may be any other number of components within the turbine section 16.

[0035] The combustion section 14 may be disposed in series between the compressor section 12 and the turbine section 16. The combustion section 14 may be fluidly coupled to at least a portion of the compressor section 12 and the turbine section 16 such that the combustion section 14 at least partially fluidly couples the compressor section 12 to the turbine section 16. As a non-limiting example, the combustion section 14 may be fluidly coupled to the HP compressor 24 at an upstream end of the combustion section 14 and to the HP turbine 26 at a downstream end of the combustion section 14.

[0036] During operation of the turbine engine 10, ambient or atmospheric air is drawn into the compressor section 12 via a fan (not shown) upstream of the compressor section 12, where it is compressed, defining pressurized air. The pressurized air may then flow into the combustion section 14, where it is mixed with fuel and ignited, thereby generating combustion gases. The HP turbine 26 extracts some work from these combustion gases, which drives the HP compressor 24. The combustion gases are exhausted to the LP turbine 28, which extracts additional work to drive the LP compressor 22, and the exhaust gases are ultimately exhausted from the turbine engine 10 via an exhaust section (not shown) downstream of the turbine section 16. The drive of the LP turbine 28 drives the LP spool, which rotates the fan (not shown) and the LP compressor 22. Together, the pressurized airflow and the combustion gases may define the working airflow flowing through the fan, compressor section 12, combustion section 14, and turbine section 16 of the turbine engine 10.

[0037] Figure 2 Describes the suitable Figure 1FIG2 is a cross-sectional view of a combustor 36 used in the combustion section 14 of FIG2. The combustor 36 may include an annularly arranged fuel nozzle assembly 38 for supplying fuel to the combustor. It should be understood that the fuel nozzle assembly 38 may be organized in any arrangement, including an annular arrangement having multiple fuel injectors. Depending on the type of engine in which the combustor 36 is located, the combustor 36 may have a can shape, a can annular arrangement, or an annular arrangement. The combustor 36 may include a combustor liner 40 having an annular inner combustor liner 41 and an annular outer combustor liner 42, a dome assembly 44 including a dome 46 and a flow guide 48, which together define a combustion chamber 50 about a longitudinal axis 52. At least one fuel nozzle 54 is fluidly coupled to the combustion chamber 50 to supply fuel to the combustor 36. The fuel nozzle 54 may be disposed within the dome assembly 44 upstream of the flared cone 56 to define a fuel outlet 58. A swirler may be provided at the dome assembly 44 to swirl the incoming air about the fuel exiting the fuel nozzles 54 and provide a uniform mixture of air and fuel entering the combustor 36 .

[0038] A first set of dilution openings or holes 60 may extend through the combustor liner 40. The first set of dilution holes 60 may extend from the annular outer combustor liner 42 to the annular inner combustor liner 41. That is, the first set of dilution holes 60 fluidly connects an interior 62 of the combustion chamber 50 with an exterior 64 of the combustion chamber 50.

[0039] Optionally, a second set of dilution openings or holes 66 may be formed through the combustor liner 40. Although shown downstream of the first set of dilution holes 60, it is contemplated that the second set of dilution holes 66 may be upstream of the first set of dilution holes 60. It is further contemplated that any number of sets of dilution holes may be included in the combustor liner 40.

[0040] Alternatively, a set of dome dilution openings or a set of dome dilution holes 68 may extend through one or more portions of the dome assembly 44. Although illustrated as extending through the deflector 48, any portion of the dome assembly 44 is contemplated.

[0041] Figure 3 A fuel nozzle assembly 100 is shown that is suitable for use as a fuel nozzle assembly 38 in a combustor 36. Figure 2), includes a fuel nozzle 102 and a swirler assembly or swirler 104 surrounding the fuel nozzle 102. The fuel nozzle 102 may define a fuel passage 106, with a nozzle cover 108 disposed in the fuel passage 106 upstream of a nozzle tip 110. The swirler 104 includes a front wall 112 and a rear wall 114, with a set of vanes 116 extending between the front wall 112 and the rear wall 114. Alternatively, the set of vanes 116 may be two sets of vanes, with a first set of vanes extending between the front wall 112 and a center wall 122, and a second set of vanes extending between the center wall 122 and the rear wall 114. The set of vanes 116 may be arranged at an angle to impart a tangential or swirl component to the airflow passing through the swirler 104. Alternatively, the first set of vanes may impart swirl in a first direction, and the second set of vanes may impart swirl in a second direction opposite the first direction.

[0042] Fuel passage 106 may be a hydrogen fuel passage that provides hydrogen fuel or a hydrogen fuel mixture to combustion chamber 50 .

[0043] The set of vanes 116 may be any structure that changes the direction of at least a portion of the airflow in the swirler 104. By way of example, the set of vanes 116 may be a portion of a wall, a protrusion from a wall, a recess in a wall, or an airfoil-shaped structure. The set of vanes 116 may have a leading edge and a trailing edge. The set of vanes 116 may have an airfoil shape similar to the circumferentially spaced stationary vanes located in the compressor section 12 or the turbine section 16.

[0044] The nozzles may be defined between the leading edges of adjacent blades of a set of blades 116. The outlets or blade outlets may be defined by the trailing edges of adjacent blades. Thus, the set of blades 116 forms a set of circumferentially spaced nozzles and a set of circumferentially spaced outlets. The set of nozzles may be fluidly coupled to the compressor section 12.

[0045] The front exterior surface 118 may be the portion of the front wall 112 that is axially farthest from the fuel passage 106. The rear exterior surface 120 may be the portion of the rear wall 114 that is axially farthest from the fuel passage 106.

[0046] A central wall 122 having a central outer surface 124 may separate the swirler 104 into a forward passage 126 and an aft passage 128, and a set of vanes 116 may be arranged as a vane group within each of the forward passage 126 and the aft passage 128. A flow splitter 130 extends behind the central wall 122 at the trailing edges of the vanes 116.

[0047] A first inlet 134 fluidly coupled to the forward passage 126 may be defined by, or between, the forward exterior surface 118 of the forward wall 112 and the central exterior surface 124 of the central wall 122. A second inlet 136 fluidly coupled to the aft passage 128 may be defined by, or between, the central exterior surface 124 of the central wall 122 and the aft exterior surface 120 of the aft wall 114. The first inlet 134 and / or the second inlet 136 may be an annular inlet or annular inlet of the swirler 104, wherein the annular inlet or annular inlet fluidly couples the compressor section 12 to the swirler 104.

[0048] At least one variable area device or adjustable flow regulator may be located at or adjacent to the first inlet 134 or the second inlet 136. The at least one flow regulator may be any suitable structure or device that regulates, changes, or modifies the flow rate of compressed air from the HP compressor section 24 to the combustor 50. It is contemplated that the at least one flow regulator may vary the flow rate into or through at least a portion of the swirler 104.

[0049] At least one flow regulator may be located near the first inlet 134 or the second inlet 136. As an example, the at least one variable area device or adjustable flow regulator is shown as a first movable wall 140 and a second movable wall 142. The first movable wall 140 is located at the front outer surface 118 and is movable axially toward the central outer surface 124. When the first movable wall 140 is adjusted or moved toward the central outer surface 124, the effective area of ​​the first inlet 134 decreases. As used herein, the term "effective area" may be equal to or proportional to the minimum cross-sectional area of ​​one or more portions of the air circuit through the swirler 104. As non-limiting examples, the air circuit may include one or more of the first inlet 134, the second inlet 136, the front passage 126, the rear passage 128, or a portion of the swirler 104 at or upstream of the nozzle tip 110 or the combustion chamber 50. The term "effective area" may further be interpreted as being equal to or proportional to the smallest cross-sectional area of ​​one or more portions of a set of dilution holes.

[0050] The effective area of ​​the first inlet 134 may depend on a first diameter 144 measured axially from the central wall 122 to the first movable wall 140 .

[0051] A second movable wall 142 is located at the rear outer surface 120 and can slide or move axially toward the central outer surface 124. When the second movable wall 142 is adjusted, slid, or otherwise moved toward the central outer surface 124, the effective area of ​​the second inlet 136 decreases. The effective area of ​​the second inlet 136 can depend on a second diameter 146 measured axially from the central wall 122 to the second movable wall 142.

[0052] The first movable wall 140 and the second movable wall 142 can define a pair of opposing walls. It is contemplated that the first movable wall 140 and the second movable wall 142 can be located on axially opposite sides of the first inlet 134 and the second inlet 136. It is further contemplated that the first movable wall 140 and the second movable wall 142 can be located on axially opposite sides of the same inlet. The first movable wall 140 and the second movable wall 142 can move toward each other or can move in the same axial direction.

[0053] The first movable wall 140 or the second movable wall 142 can be used to control the velocity of the airflow mixed with the fuel. It is contemplated that adjusting the first movable wall 140 or the second movable wall 142 can be used to vary the pressure drop. That is, the first movable wall 140 or the second movable wall 142 can be used to achieve a predetermined or customized pressure drop. The pressure drop can be between the first inlet 134 or the second inlet 136 and the annular outlet or outlet 147 that fluidly couples the swirler 104 to the combustion chamber 50. It is further contemplated that adjusting the first movable wall 140 or the second movable wall 142 can be used to vary the volumetric flow rate or direction of the airflow mixed with the fuel.

[0054] Although illustrated as a first movable wall 140 and a second movable wall 142, the at least one adjustable flow regulator can be any shape capable of blocking one or more portions of the first inlet 134 or the second inlet 136 via linear or angular motion. That is, it is contemplated that the at least one adjustable flow regulator can be a rotatable flow regulator. Although two inlets and two flow regulators are depicted, any number of inlets or flow regulators is contemplated.

[0055] While illustrated as radial-radial flow, it is contemplated that the swirler 104 may be an axial-radial swirler or any known swirler in which at least one adjustable flow regulator may block one or more portions of at least one inlet of a passage defined by the swirler.

[0056] The at least one adjustable flow regulator may be controlled using one or more external or internal actuation mechanisms, such as, but not limited to, a hydraulic ram or an electric motor 148 .

[0057] A sensor 150 may be located in the fuel passage 106. The sensor 150 may be a flow meter. The sensor 150 may provide an output indicating the flow rate of fluid through the fuel passage 106. The variable area device or adjustable flow regulator may be automatically adjusted based on the flow rate of fluid in the fuel passage 106 measured or determined by the sensor 150. Additionally or alternatively, the sensor 150 may measure or provide an output indicating a pressure drop across one or more portions of the swirler 104. For example, the sensor 150 may provide a pressure drop between the first inlet 134 or the second inlet 136 and the outlet 147 or the combustion chamber 50. Although illustrated as a pressure drop between the first inlet 134 or the second inlet 136 and the outlet 147, the pressure drop may be measured between any point in the swirler 104 and another point in the swirler 104 or any location in the combustion chamber 50.

[0058] Actuation of the at least one adjustable flow regulator may be caused by one or more outputs of the sensor 150. That is, the first movable wall 140 or the second movable wall 142 may be automatically adjusted based on the fuel flow or pressure drop determined by the sensor 150.

[0059] It is contemplated that the sensor 150 may function as an actuator, wherein the output of the sensor is a physical movement initiated by the sensor 150 and communicated, for example, through a linkage, to the first movable wall 140 or the second movable wall 142. That is, the sensor 150 may directly control the effective area of ​​the first inlet 134 or the second inlet 136 based on fuel flow or pressure differential.

[0060] Although illustrated as a single sensor 150 , any number of sensors adjacent to or within the fuel nozzle assembly 100 is contemplated.

[0061] Because of the large annular flow from the HP compressor section 24 to the combustor, a typical inline valve will not function as at least one adjustable flow regulator. That is, the flow from the HP compressor section 24 cannot be contained in a simple pipe with an inline valve. At least one flow regulator must be able to handle the flow from the HP compressor section 24 ( Figure 1 ) and selectively provides compressed air to the first inlet 134 or the second inlet 136.

[0062] Figure 4 A fuel nozzle assembly 200 is shown that is suitable for use as the fuel nozzle assembly 38 in the combustor 36 (see FIG. Figure 2The fuel nozzle assembly 200 is similar to the fuel nozzle assembly 100, with slightly different parts added. The fuel nozzle assembly 200 includes the fuel nozzle 102 and a swirler 204 surrounding the fuel nozzle 102. The fuel nozzle 102 defines a fuel passage 106, with a nozzle cover 108 disposed in the fuel passage 106 upstream of the nozzle tip 110. The swirler 204 includes an annular front wall 212 and an annular rear wall 214, with a set of vanes 216 extending between the front wall 212 and the rear wall 214.

[0063] Center wall 222 may separate swirler 204 into forward and aft passages 226, 228, and vanes 216 may be arranged as vane groups within each of forward and aft passages 226, 228. Splitter 230 may extend behind center wall 222 at the trailing edges of vanes 216.

[0064] As an example, at least one variable area device or adjustable flow regulator is illustrated as a set of vanes 216 and one or more actuators that pivot at least one vane in the set of vanes 216. That is, the set of vanes 216 can be coupled to one or more actuators. As an example, the one or more actuators are illustrated as a first actuator 254 and a second actuator 256. As an example, the first actuator 254 is illustrated as being at least partially located within the front wall 212, while the second actuator 256 is illustrated as being at least partially located within the rear wall 214. Other locations for the one or more actuators are contemplated, such as, but not limited to, within the set of vanes 216, the center wall 222, an outer portion of the front wall 212, or an outer portion of the rear wall 214. The one or more actuators can also be located outside the turbine engine 10 using a connecting rod (i.e., a rod, cable, or rod) in communication with the vanes 216.

[0065] The first actuator 254 or the second actuator 256 can cause one or more blades in the set of blades 216 to rotate about the pivot 258. The first actuator 254 and the second actuator 256 can cause one or more blades in the set of blades 216 to rotate about the pivot 258. That is, the first actuator 254 and / or the second actuator 256 can cause one or more blades in the set of blades 216 to rotate by applying a force on one or more portions of the set of blades 216 at a non-zero distance from the pivot 258 that causes rotation about the pivot 258. Although illustrated as being located at the center of each blade in the set of blades 216, any location on the pivot 258, each blade, including varying locations from one blade to another, is contemplated.

[0066] Rotating one or more vanes in set of vanes 216 may change the effective area of ​​forward passage 226, first inlet 234 of forward passage 226, aft passage 228, or second inlet 236 of aft passage 228. In other words, set of vanes 216 may be a variable area device. Furthermore, the velocity of the airflow mixed with the fuel may be controlled, at least in part, by rotating one or more vanes in set of vanes 216.

[0067] Adjustment of the set of vanes 216 via the first and second actuators 254 and 256 may be used to vary the pressure drop. As an example, the pressure drop may be between the first or second inlet 234, 236 and the outlet 247 where the swirler 204 is fluidly coupled to the combustor 50.

[0068] It is contemplated that adjustment of the set of vanes 216 via the first actuator 254 or the second actuator 256 may be automated based on output from the sensor 150. The output from the sensor 150 may indicate a fuel flow rate in the fuel passage 106, or a pressure drop between one or more portions of the swirler 204 and the combustion chamber 50. It is further contemplated that adjustment of the set of vanes 216 via the first actuator 254 or the second actuator 256 may be determined by one or more controllers based on the output of the sensor 150.

[0069] Alternatively, the fuel nozzle assembly 200 may include a first movable wall 140 and a second movable wall 142. The first movable wall 140 or the second movable wall 142 may be controlled by a sensor 150 or moved based on an output provided by the sensor 150.

[0070] Steering Figure 5 , along Figure 4 Section VV of FIG. 2 shows a set of vanes 216 arranged radially relative to the front wall 212, taken between the front wall 212 and the central wall 222. The set of vanes 216 can rotate, for example, about a pivot 258, as indicated by arrow 260 and illustrated by the imaginary rotating vane 217. The set of vanes 216 can be controlled individually or moved together. That is, the variable area device can cause a single vane or a group of vanes in a set of vanes 216 to pivot separately through an arc that is different from the arc of the remaining vanes in the set of vanes 216. Each vane in the set of vanes 216 can be rotated clockwise or counterclockwise through an arc to change the effective area of ​​the front passage 226 or the rear passage 228 upstream of the outlet 247.

[0071] Figure 6 A fuel nozzle assembly 300 is shown that is suitable for use as the fuel nozzle assembly 38 in the combustor 36. The fuel nozzle assembly 300 is similar to Figure 3 The fuel nozzle assembly 100 and Figure 4The fuel nozzle assembly 200 is shown with slightly different parts added. The fuel nozzle assembly 300 includes the fuel nozzle 102 and a swirler 304 surrounding the fuel nozzle 102. The fuel nozzle 102 may define a fuel passage 106, with a nozzle cover 108 disposed in the fuel passage 106 upstream of the nozzle tip 110. The swirler 304 includes an annular front wall 312 and an annular rear wall 314, with a set of vanes 316 extending between the front wall 312 and the rear wall 314.

[0072] Central wall 322 may separate swirler 304 into forward and aft passages 326, 328, and a set of vanes 316 may be disposed within each of forward and aft passages 326, 328. Splitter 330 may extend behind central wall 322 at the trailing edges of set of vanes 316.

[0073] A set of blades 316 may be surrounded by a baffle, which is illustrated as including at least one opening or window 372 (see FIG. Figure 7 ) is provided with a perforated ring 370. Flow to the first inlet 334 of the front channel 326 and the second inlet 336 of the rear channel 328 can be controlled by the perforated ring 370. Alternatively, the perforated ring 370 can be more than one baffle or perforated ring, wherein a first perforated ring controls flow through the first inlet 334 of the front channel 326 and a second perforated ring can control flow through the second inlet 336 of the rear channel 328. That is, any number of baffles or perforated rings is contemplated.

[0074] Optionally, perforated ring 370 can rotate or move axially. Rotation or axial movement of perforated ring 370 can change the effective area of ​​first inlet 334 of front passage 326 or second inlet 336 of rear passage 328. In other words, perforated ring 370 is a variable area device. The velocity of the airflow mixed with the fuel can be controlled at least in part by rotation or movement of perforated ring 370.

[0075] Additionally or alternatively, adjustment of the perforated ring 370 may be used to vary the pressure drop. For example, the pressure drop may be between the first inlet 334 or the second inlet 336 and the outlet 347 where the swirler 304 is fluidly coupled to the combustion chamber 50.

[0076] Although illustrated as being external to the front and rear channels 326 , 328 , it is contemplated that one or more portions or all of the perforated rings 370 are located within the front and rear channels 326 , 328 .

[0077] Optionally, an actuator 371 may be engaged with the perforated ring 370. The actuator 371 may be in direct communication with or directly controlled by the sensor 150. The output from the sensor 150 may indicate the fuel flow rate in the fuel passage 106 or the pressure drop between one or more portions of the swirler 304 and the combustion chamber 50. The actuator 371 or the sensor 150 may automatically adjust the perforated ring 370 or provide an output for adjusting the perforated ring 370.

[0078] Additionally or alternatively, the actuator 371 can be in communication with one or more controllers. It is contemplated that the actuator 371 can rotate or move the perforated ring 370 relative to the first inlet 334 or the second inlet 336. It is further contemplated that the actuator 371 can adjust the at least one opening or window 372 (see Figure 7 ) effective area.

[0079] Steering Figure 7 , along Figure 6 Section VII-VII of FIG. 3 shows a set of blades 316 arranged radially relative to the front wall 312, between the front wall 312 and the central wall 322. The perforated ring 370 can be used to control the first inlet 334 or the second inlet 136 ( Figure 6 ) effective area. Alternatively, actuator 371 can control perforated ring 370 as it rotates relative to first inlet 334 or second inlet 136. As it rotates, perforated ring 370 can control the effective area of ​​first inlet 334 or second inlet 136 as it moves from a solid portion 374 of perforated ring 370 to an open portion (such as at least one window 372). Similarly, the velocity of the air flow mixed with the fuel can be controlled by the rotation or rotational speed of perforated ring 370.

[0080] Additionally or alternatively, adjustment of the size of the windows 372 or the rotational speed of the perforated ring 370 can be used to vary the control of the pressure drop. That is, as shown by way of example, the windows 372 can be equally spaced or equally sized. Alternatively, one or more of the spacing or size can vary from one window 372 to another. Furthermore, it is contemplated that features that vary the size of the windows 372 can be added to the perforated ring 370.

[0081] Figure 8A sensor or actuator 400 is shown that can be used as or coupled to any sensor or actuator as described herein. The actuator 400 can include a housing 402 surrounding a piston 404. A piston seal 406 can fluidically isolate a first chamber 408 from a second chamber 410. A fluid inlet / outlet 412 can extend through the housing 402 and fluidically couple the first chamber 408 to a fluid source. The fluid source can be the fuel passage 106 or a separate fluid reservoir (not shown).

[0082] The piston 404 can have a position return device such as a spring 414. The spring 414 can be located in the second chamber 410 and surround at least a portion of the piston 404. The second chamber 410 can be a dry chamber, that is, the second chamber 410 can include air as the fluid through which the components are connected. The vent 416 can fluidly connect the second chamber 410 to the exterior 420 of the housing 402.

[0083] The piston rod 422 driven by the fluid pressure in the first chamber 408 can be coupled to one or more components that control the effective area or pressure differential of the fuel nozzle 102. That is, the piston rod 422 can be used to control Figure 3-6 One or more elements at or near the first inlet 134 , 234 , 334 or the second inlet 136 , 236 , 336 of the cyclone 104 , 204 , 304 .

[0084] When the fluid pressure in the first chamber 408 increases, the piston 404 can be actuated to compress the spring 414 in the second chamber 410. This causes the piston rod 422 to extend. When the fluid pressure in the first chamber 408 decreases, the spring 414 restores the position of the piston rod 422 and the volume of the fluid in the first chamber 408 decreases.

[0085] It is contemplated that one or more portions of the actuator 400 may be coupled to Figure 3-6 The sensor 150 or the fuel passage 106 is in communication with or included in Figure 3-6 sensor 150 or in fuel passage 106 .

[0086] Figure 9AA sensor or actuator 500 is shown, which can be used with or coupled to any sensor or actuator as described herein. Actuator 500 can include a housing 502 surrounding a piston 504. A piston seal 506 can fluidically isolate a first chamber 508 from a second chamber 510. A first fluid inlet / outlet 512 can extend through housing 502 and fluidically couple first chamber 508 to a fluid source. The fluid source can be fuel passage 106 or a first fluid reservoir or first reservoir 511. A second fluid inlet / outlet 516 can extend through housing 502 and fluidically couple second chamber 510 to a fluid source, illustrated as a second fluid reservoir or second reservoir 513. One or more pumps (not shown) can be located at or between first reservoir 511 and first inlet / outlet 514. Optionally, one or more additional pumps can be located at or between second reservoir 513 and second fluid inlet / outlet 516.

[0087] The piston rod 522 can be driven by the volume or pressure of the fluid in the first chamber 508 or the second chamber 510. As shown, as an example, fluid 524 can enter the first chamber 508. The fluid 524 can be pumped into the first chamber 508 from the first reservoir 511 or forced into the first chamber 508 due to an increase in pressure in the first reservoir 511. When the volume or pressure of the fluid in the first chamber 508 increases, the piston 504 is pushed toward the second chamber 510. This reduces the volume of the second chamber 510 and can force the fluid from the second chamber 510 into the second reservoir 513.

[0088] Alternatively, when fluid from the second chamber 510 is drawn into the second reservoir 513 by a pump or a change in pressure in the second reservoir 513, the piston 504 may be pulled toward the second chamber 510. The resulting increase in volume of the first chamber 508 draws fluid from the first reservoir 511 into the first chamber 508.

[0089] Figure 9B The actuator 500 is shown in an alternative situation in which the piston 504 is pulled toward the first chamber 508. As shown, as an example, fluid 524 can exit the first chamber 508. The fluid 524 can be pumped out of the first chamber 508 and into the first reservoir 511, or forced into the first reservoir 511 due to an increase in pressure in the first chamber 508. When the volume of the fluid in the first chamber 508 decreases, the piston 504 moves toward the first chamber 508. This increases the volume of the second chamber 510 and can force fluid from the second reservoir 513 into the second chamber 510.

[0090] Alternatively, the piston 504 may be pulled toward the first chamber 508 when fluid from the second reservoir 513 is pumped or drawn into the second chamber 510 by a pump or a change in pressure in the second reservoir 513. The resulting increase in volume of the second chamber 510 may cause fluid from the first chamber 508 to be forced into the first reservoir 511.

[0091] Whether pulling toward the first chamber 508 or the second chamber 510, the piston 504 can be moved as needed based on the controller or information such as the sensor 150 ( Figure 3 、 4 , and 6) to move the piston rod 522. The piston rod 522 can be connected to one or more components that control the effective area or pressure difference of the fuel nozzle 102. That is, the piston rod 522 can be used to control Figure 3-6 One or more elements at or near the first inlet 134 , 234 , 334 or the second inlet 136 , 236 , 336 of the cyclone 104 , 204 , 304 .

[0092] Figure 10 Describes the suitable Figure 1 A cross-sectional view of a burner 636 used in the combustion section 14 of FIG. The burner 636 is similar to Figure 2 The combustor 36 of FIG. 3 includes at least one flow conditioner that can be located adjacent to the first set of dilution holes 60 . As an example, the at least one variable area device or adjustable flow conditioner is shown as a first movable wall 640 . The first movable wall 640 is located on the annular outer combustor liner 42 of the combustor liner 40 , adjacent to the first set of dilution holes 60 . The first movable wall 640 is axially movable. That is, the first movable wall 640 can move back and forth along the surface of the annular outer combustor liner 42 . When the first movable wall 640 is adjusted or moved to cover the first inlet 635 of the first set of dilution holes 60 , the effective area of ​​the first inlet 635 is reduced.

[0093] The effective area of ​​the first inlet 635 may depend on a first diameter 645 measured axially from the first movable wall 640 to the opposing sidewall 655 of the first set of dilution holes 60. Although shown downstream of the first inlet 635, it is contemplated that the first movable wall 640 may be upstream of the first inlet 635.

[0094] Optionally, a second movable wall 642 can be located at the annular outer combustor liner 42 of the combustor liner 40, adjacent the second set of dilution holes 66. When the second movable wall 642 is adjusted, slid, or otherwise moved, it can at least partially cover the second inlet 637 of the second set of dilution holes 66. When the second movable wall 642 covers at least a portion of the second inlet 637, the effective area of ​​the second inlet 637 is reduced. The effective area of ​​the second inlet 637 can be determined by a second diameter 665 measured axially from a leading edge of the second movable wall 642 to a side of the second inlet 637 farthest from the second movable wall 642.

[0095] The first inlet 635 or the second inlet 637 may be an annular inlet or annular inlet of the combustor 50 , wherein the annular inlet or annular inlet fluidly couples the compressor section 12 to the combustor 50 .

[0096] The first movable wall 640 and the second movable wall 642 can define a pair of opposing walls. It is contemplated that the first movable wall 640 and the second movable wall 642 can be located on axially opposite sides of the first inlet 635 and the second inlet 637. It is further contemplated that the first movable wall 640 and the second movable wall 642 can be located on axially opposite sides of the same inlet. The first movable wall 640 and the second movable wall 642 can slide or move toward each other, or can move in the same axial direction.

[0097] It is contemplated that the first movable wall 640 and the second movable wall 642 may be controlled, actuated, or moved together. Alternatively, the first movable wall 640 and the second movable wall 642 may be independently moved, actuated, or otherwise controlled. Further, control of the first movable wall 640 or the second movable wall 642 may be dependent upon one or more sensors in one or more portions of the combustor 36, including but not limited to the swirler 104 (see FIG. Figure 3 ).

[0098] While the first set of dilution holes 60 is illustrated adjacent to the combustor liner 40, it is contemplated that at least the first movable wall 640 may be used to control the effective area of ​​a set of domed dilution holes 68. That is, any number of the movable walls may be moved radially, axially, or at an angle relative to the longitudinal axis 52 to vary the effective area of ​​any one or more sets of dilution holes.

[0099] Figure 11 Describes the suitable Figure 1 FIG. 7 is a cross-sectional view of a burner 736 used in combustion section 14. Burner 736 is similar to burner 636, with slightly different parts added.

[0100] Flow to the first inlet 635 of the first set of dilution holes 60 can be controlled by a first baffle or first perforated ring 770. Optionally, a second baffle or second perforated ring 773 can control flow through the second inlet 637. Alternatively, a single baffle or perforated ring can control flow through the first inlet 635 and the second inlet 637. That is, any number of baffles or perforated rings is contemplated.

[0101] Alternatively, first perforated ring 770 can rotate or move axially. Rotation or axial movement of first perforated ring 770 can change the effective area of ​​first inlet 635. Similarly, second perforated ring 773 can move axially or rotate to control the effective area of ​​second inlet 637. That is, first perforated ring 770 and second perforated ring 773 are examples of variable area devices.

[0102] It is contemplated that the first perforated ring 770 or the second perforated ring 773 can be controlled, actuated, or moved together. Alternatively, the first perforated ring 770 and the second perforated ring 773 can be independently moved, actuated, or otherwise controlled. It is contemplated that the first perforated ring 770 or the second perforated ring 773 can rotate about the longitudinal axis 52. The rotational speed or angle of the first perforated ring 770 or the second perforated ring 773 can be controlled or adjusted by a controller (not shown) or any combination of sensors or actuators.

[0103] While illustrated adjacent the first set of dilution holes 60 in the combustor liner 40, it is contemplated that at least the first perforated ring 770 may be used to control the effective area of ​​a set of domed dilution holes 68. That is, any number of perforated rings that may be rotated from solid portions to open windows relative to the longitudinal axis 52 may be used to control the effective area of ​​one or more sets of openings or dilution holes in the combustor 736.

[0104] Steering Figure 12 , along Figure 11 , taken at section XII-XII of FIG. 5 , at the first set of dilution holes 60. A first perforated ring 770 can be used to control the effective area of ​​the first inlet 635. The first perforated ring 770 can control the effective area of ​​the first inlet 635 as it rotates from a solid portion 774 of the first perforated ring 770 to an open portion, such as at least one window 772, as indicated by arrow 780. Circumferentially spaced windows 772 can surround at least one annular inlet or first inlet 635. Rotation of the first perforated ring 770 can be clockwise or counterclockwise, as indicated by arrow 780. While illustrated as closing or fully covering the first inlet 635, it is contemplated that the first perforated ring 770 can be rotated to partially cover or fully uncover or open the first inlet 635 to fluidly couple the interior 62 of the combustion chamber 50 to the exterior 64 of the combustion chamber 50.

[0105] Additionally or alternatively, adjustment of the size of the windows 772 or the rotational angle of the first perforated ring 770 can be used to vary the effective area or velocity of airflow through the first set of dilution holes 60. As shown as an example, the windows 772 can have varying sizes or spacing. Alternatively, one or more spacings or sizes can be the same from one window 772 to another. Further, it is contemplated that features that vary the size or shape of the windows 772 can be added to the first perforated ring 770.

[0106] Although illustrated as having varying sizes and spacing, it is contemplated that the first inlets 635 may be the same size first inlets 635 or evenly spaced in a circumferential arrangement about the combustion chamber 50 .

[0107] Benefits of aspects of the present disclosure include air flow velocity control that can be used to avoid high shear forces between two or more swirling air flows.

[0108] Furthermore, aspects of the present disclosure may be used to generate high velocity airflow on the swirler outer diameter and the fuel nozzle outer diameter to avoid flame holding.

[0109] The movable wall near the swirler inlet allows air flow customization for each circuit based on the needs of operating conditions.Air flow customization can allow high speeds on the fuel nozzle outer diameter in low power conditions to avoid flame holding on the fuel nozzle.

[0110] Other aspects of the present disclosure provide for controlling the pressure drop or effective area of ​​one or more passages of air entering a fuel nozzle or defined by a swirler.

[0111] The ability to control the pressure drop, velocity, volumetric flow rate, effective area, or direction of the air flow from the HP compressor section to the combustor at one or more combustor inlets allows the use of fuels with higher combustion temperatures, such as hydrogen. Control of the air flow allows the flame shape and position to be customized for each operating condition. In other words, controlling the air flow velocity and velocity profile and customizing it for each operation can reduce flame holding or flashback, which is particularly beneficial for fuels with high flame speeds.

[0112] Additional benefits include air flow control through the swirler based on the fuel flow rate measured, for example, by a sensor. That is, the air flow control may be automatic or varied in response to a measured or calculated fuel flow rate.

[0113] Air flow control through the swirler can also be independent of the fuel flow rate.

[0114] Actuation of a set of vanes can change the swirl number and therefore the flame shape.

[0115] As such, it should be understood that the examples used herein are not specifically limited to those shown, and those skilled in the art should understand that aspects from one or more examples may be mixed and / or combined with one or more aspects from other examples to define examples that may differ from those shown.

[0116] 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 may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they include 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 language of the claims.

[0117] Further aspects of the present disclosure are provided by the subject matter of the following clauses:

[0118] 14. The invention relates to a turbine engine comprising: a compressor section, a combustion section, and a turbine section in a serial flow arrangement, the combustion section comprising: a combustor liner; a dome assembly coupled to the combustor liner; a fuel nozzle fluidly coupled to the dome assembly; a combustion chamber fluidly coupled to the fuel nozzle and at least partially defined by the combustor liner and the dome assembly; at least one set of dilution openings located in the dome assembly or the combustor liner and fluidly coupled to the combustion chamber; a swirler defining at least one passage extending between at least one annular inlet and at least one annular outlet, wherein the at least one annular inlet is fluidly coupled to the compressor section; at least one set of vanes located in the at least one passage and arranged circumferentially about the fuel nozzle; and a variable area device movable to vary an effective area of ​​at least a portion of the at least one set of dilution openings or the swirler.

[0119] Turbine engine according to the preceding clause, wherein the variable area device comprises at least one movable wall which, when moved, varies the effective area of ​​the at least one set of dilution openings or the at least one portion of the swirler.

[0120] Turbine engine according to any of the preceding clauses, wherein said at least one movable wall is slidably movable over said at least one set of dilution openings or said at least one portion of said swirler.

[0121] Turbine engine according to any of the preceding clauses, wherein the at least one movable wall comprises a pair of opposing walls.

[0122] Turbine engine according to any of the preceding clauses, wherein each wall of the pair of opposing walls is located on axially opposite sides of the inlet of the at least one set of dilution openings or the at least one portion of the swirler.

[0123] A turbine engine according to any of the preceding clauses, wherein the opposing walls are slidably movable towards each other.

[0124] The turbine engine according to any of the preceding clauses, further comprising a fuel passage, wherein at least one sensor or actuator is in fluid communication with the fuel passage.

[0125] A turbine engine according to any of the preceding clauses, wherein the variable area device is automatically adjusted based on fluid flow in the fuel passage as determined by the sensor or the actuator.

[0126] The turbine engine according to any of the preceding clauses, further comprising a fuel passage fluidly coupled to the combustion chamber, wherein the fuel passage is a hydrogen fuel passage providing hydrogen fuel or a hydrogen fuel mixture to the combustion chamber downstream of the at least one annular outlet.

[0127] The turbine engine according to any of the preceding clauses, wherein the variable area device pivots at least one blade of the at least one set of blades, wherein pivoting the at least one blade through an camber varies the effective area of ​​the at least one passage.

[0128] The turbine engine according to any of the preceding clauses, wherein the variable area devices cause the groups of blades of the at least one set of blades to pivot separately through a different camber than the remaining subsets of the set of blades.

[0129] Turbine engine according to any of the preceding clauses, wherein the variable area device comprises a baffle having a plurality of circumferentially spaced windows surrounding at least a portion of the at least one set of dilution openings or the swirler.

[0130] Turbine engine according to any of the preceding clauses, wherein the plurality of circumferentially spaced windows are equally spaced.

[0131] The turbine engine according to any of the preceding clauses, wherein the plurality of circumferentially spaced windows are of the same size.

[0132] Turbine engine according to any of the preceding clauses, wherein rotation of the baffle or axial movement of the baffle varies the effective area of ​​at least one set of dilution openings or at least a portion of the swirler.

[0133] The turbine engine according to any of the preceding clauses, wherein the at least one set of blades comprises at least a first set of blades and a second set of blades, the second set of blades being axially spaced from the first set of blades.

[0134] A swirler assembly for a combustor of a turbine engine, the swirler assembly comprising: a swirler defining at least one passage extending between at least one annular inlet and at least one annular outlet; at least one set of vanes positioned in the at least one passage; and a variable area device movable to vary the effective area of ​​at least a portion of the swirler.

[0135] A swirler assembly according to any of the preceding clauses, wherein the variable area device comprises at least one movable wall which, when moved, causes the effective area of ​​the at least one annular inlet to vary.

[0136] The swirler assembly of any of the preceding clauses, wherein the variable area device pivots at least one vane of the at least one set of vanes and allows pivotal movement of the at least one vane through an arc to vary the effective area of ​​the at least one passage.

[0137] A swirler assembly according to any of the preceding clauses, wherein the variable area device comprises a baffle having a plurality of circumferentially spaced windows surrounding the at least one annular inlet, whereby rotation or axial movement of the baffle causes the effective area of ​​the at least one annular inlet to vary.

Claims

1. A turbine engine, characterized in that: include: a compressor section, a combustion section, and a turbine section in a serial flow arrangement defining an axis of rotation extending from front to rear, the combustion section comprising: burner lining; a dome assembly coupled to the combustor liner; a fuel nozzle terminating in a nozzle tip and coupled to the dome assembly; a combustion chamber fluidly coupled to the fuel nozzle and defined at least in part by the combustor liner and the dome assembly; a swirler positioned forward of the nozzle tip and surrounding the fuel nozzle, the swirler comprising: a front wall comprising a front exterior surface; a rear wall spaced from the front wall and comprising a rear exterior surface; a central wall disposed between the front wall and the rear wall, defining a front channel and a rear channel; a first variable area device located at the front outer surface and slidable along the front outer surface toward the rear to reduce the effective area of ​​the front channel; and A second variable area device is located at the rear outer surface and is slidable along the rear outer surface toward the front to reduce an effective area of ​​the rear passage.

2. The turbine engine according to claim 1, characterized in that Further included is a fuel passage, wherein at least one sensor or at least one actuator is in fluid communication with the fuel passage.

3. The turbine engine according to claim 2, characterized in that Wherein the first variable area device and the second variable area device are automatically adjusted based on fluid flow in the fuel passage determined by the at least one sensor or the at least one actuator.

4. The turbine engine according to claim 1, characterized in that Further included is a fuel passage fluidly coupled to the combustion chamber, wherein the fuel passage is a hydrogen fuel passage that provides hydrogen fuel or a hydrogen fuel mixture to the combustion chamber.

5. The turbine engine according to claim 1, characterized in that Wherein at least one of the first variable area device or the second variable area device comprises a baffle having a plurality of circumferentially spaced windows surrounding at least a portion of the swirler.

6. The turbine engine according to claim 5, characterized in that wherein the plurality of circumferentially spaced windows are equally spaced.

7. The turbine engine according to claim 6, characterized in that wherein the plurality of circumferentially spaced apart windows are of equal size.

8. The turbine engine according to claim 5, characterized in that The rotation of the baffle or the axial movement of the baffle changes the effective area of ​​at least a portion of the swirler.

9. The turbine engine according to claim 1, characterized in that Wherein the front wall and the central wall define a first inlet for the front channel, and wherein the first variable area device is positioned exterior to the first inlet.

10. The turbine engine according to claim 9, characterized in that Wherein the central wall and the rear wall define a second entrance for the rear passage, and wherein the second variable area device is positioned rearward of the first variable area device.

11. The turbine engine according to claim 1, characterized in that Further included is a flow splitter extending from the central wall, the flow splitter at least partially defining the front channel and the rear channel.

12. The turbine engine according to claim 11, characterized in that The flow divider is thereby turned from a radial direction to an axial direction.

13. The turbine engine according to claim 11, characterized in that The flow diverter terminates in front of the nozzle tip.

14. The turbine engine according to claim 13, characterized in that wherein the rear wall terminates within the combustion chamber.

15. The turbine engine according to claim 11, characterized in that Further included is a nozzle cover positioned within the fuel nozzle and terminating forward of the nozzle tip, wherein a rearward end of the flow splitter is aligned with the nozzle cover.

16. The turbine engine according to claim 1, characterized in that Wherein the central wall includes a central outer surface, and wherein the first variable area device is slidable along the front outer surface toward the central outer surface, and wherein the second variable area device is slidable along the rear outer surface toward the central outer surface.

17. The turbine engine according to claim 1, characterized in that Wherein the first variable area device is capable of moving independently of the second variable area device.

18. A swirler assembly for a combustor of a turbine engine, characterized in that: The cyclone assembly comprises: a fuel nozzle terminating in a nozzle tip; a swirler surrounding the fuel nozzle and positioned forward of the nozzle tip, the swirler comprising: a front wall defining a front exterior surface; a rear wall spaced from the front wall and defining a rear exterior surface; a central wall disposed between the front wall and the rear wall, defining a front channel at the front wall and a rear channel at the rear wall; a first variable area device surrounding the front channel and movable along the front exterior surface toward the rear channel to reduce an effective area of ​​the front channel; and A second variable area device surrounds the rear channel and is movable along the rear exterior surface toward the front channel to reduce an effective area of ​​the rear channel.

19. The cyclone assembly according to claim 18, characterized in that Wherein the first variable area device comprises a baffle having a plurality of circumferentially spaced windows surrounding the front channel.

20. The cyclone assembly according to claim 18, wherein The swirler further comprises a flow splitter extending from the central wall, wherein the flow splitter terminates at the nozzle tip.

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