Turbo engine fuel mixer

Abstract

A turbocharged engine may include a compressor section, a combustion section, and a turbine section arranged in a series flow configuration. The combustion section may include a combustor with a fuel mixer. The fuel mixer may include an outer wall defining a longitudinal direction and having a mixture outlet, a first compressed air flow passage, and a second compressed air flow passage.

Description

[0001] Cross-reference to related applications

[0002] This application claims priority to Indian Patent Application No. 202211005165, filed on January 31, 2022, the entire contents of which are incorporated herein by reference. Technical Field

[0003] This topic generally relates to gas turbine engine combustors, and more specifically, to fuel mixers in turbine engines. Background Technology

[0004] A gas turbine engine includes a turbine driven by the combustion of combustible fuel within the engine's combustor. The turbine engine utilizes a fuel nozzle assembly to inject combustible fuel into the combustor. This fuel nozzle assembly mixes the fuel with air before injection 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 diagram of a turbine engine with a compression section, a combustion section and a turbine section, based on the various aspects described in this article.

[0007] Figure 2 It is based on the various aspects described in this article along Line II-II. Figure 1 A cross-sectional view of the combustion zone.

[0008] Figure 3 It is based on the various aspects described in this article. Figure 2 The section of line III-III Figure 2 A cross-sectional view of the combustion zone.

[0009] Figure 4 Based on the various aspects described in this article, it is possible to... Figure 3 A perspective view of a fuel mixer used in a burner, showing at least one fuel nozzle assembly.

[0010] Figure 5 It is based on the various aspects described in this article. Figure 4 The line AA intercepted Figure 4 A side cross-sectional view of the first fuel nozzle assembly, showing the fuel nozzle.

[0011] Figure 6 yes Figure 4 A side view of the first fuel nozzle assembly, showing the channel angle.

[0012] Figure 7 It is the section AA along the line. Figure 4 A side cross-sectional view of the first fuel nozzle assembly, showing the fuel outlet.

[0013] Figure 8 It is a section taken along line BB. Figure 4 A side cross-sectional view of the second fuel nozzle assembly, showing another fuel outlet.

[0014] Figure 9 It is a cut along the CC line. Figure 4 A side cross-sectional view of the third fuel nozzle assembly, showing another fuel outlet.

[0015] Figure 10 yes Figure 4 A schematic diagram of the second fuel nozzle assembly, showing the common flow channel in the converging configuration.

[0016] Figure 11 yes Figure 4 A schematic diagram of the third fuel nozzle assembly shows another common flow channel in the divergent configuration.

[0017] Figure 12 It is a cut along the BB line based on the various aspects described in this article. Figure 4 A cross-sectional view of the second fuel nozzle assembly.

[0018] Figure 13 It is a cut along the DD line based on the various aspects described in this article. Figure 4 A cross-sectional view of the fourth fuel nozzle assembly. Detailed Implementation

[0019] The aspects disclosed herein relate to fuel nozzles 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, or more specifically, to fuel nozzle structures configured for use with elevated combustion engine temperatures, such as those using hydrogen fuel. Hydrogen fuel eliminates carbon emissions, but presents challenges related to flame retention due to its high flame velocity. Current combustors using this fuel or other high-temperature fuels include durability risks due to flame retention on combustor components caused by backfire. For illustrative purposes, this disclosure is described in relation to a turbine engine of an aircraft with 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 within engines, including but not limited to turbojet engines, turboprop engines, turboshaft engines, and turbofan engines. The aspects of the disclosure discussed herein can also have general applicability within non-aircraft engines with combustors, such as in other mobile applications and non-mobile industrial, commercial, and residential applications.

[0020] Reference will now be made in detail to the combustor architecture, particularly to the fuel nozzles used to supply fuel to the combustor located within the turbine engine, one or more examples of which are shown 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 parts of this disclosure.

[0021] 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.

[0022] As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the individual components.

[0023] The terms "forward" and "rearward" refer to relative positions within a gas turbine engine or vehicle, and specifically to the normal operating posture of the gas turbine engine or vehicle. For example, for a gas turbine engine, "forward" refers to a position closer to the engine inlet, while "rearward" refers to a position closer to the engine nozzle or exhaust port.

[0024] 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 "forward" indicate being in front of something, and "backward" or "backward" indicate being behind something. For example, when used in relation to fluid flow, forward / forward can indicate upstream, and backward / backward can indicate downstream.

[0025] 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.

[0026] Additionally, 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.

[0027] All directional references (e.g., radial, axial, proximal, distal, up, down, upward, downward, left, right, lateral, front, rear, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, backward, etc.) are used for identification purposes only to 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.

[0028] 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.

[0029] 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 the 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.

[0030] Regarding pipes or flow paths, such as those in which a heat exchanger is located, “substantially annular” means a completely annular pipe or flow path (i.e., extending continuously and uninterruptedly in the circumferential direction except for the heat exchanger alone), or a partially annular pipe or flow path having at least 50% of the volume of voids other than the heat exchanger (such as at least 60%, at least 70%, at least 80%, at least 90% of the volume of voids other than the heat exchanger).

[0031] In some exemplary embodiments of this disclosure, a turbine engine is provided that defines a centerline and a circumferential direction. The gas turbine engine generally includes a turbine and a rotor assembly. The rotor assembly may be driven by the turbine. The turbine, rotor assembly, or both may define a substantially annular flow path relative to the centerline of the gas turbine engine. The turbine engine includes a combustor located upstream of the turbine, configured to drive the turbine.

[0032] The combustor introduces pre-mixed fuel from the fuel nozzle and then burns it within the combustor to drive the turbine. Increased efficiency and reduced emissions have driven the demand for fuels that burn more cleanly or at higher temperatures, such as hydrogen fuel. There is a need to improve combustor durability under these operating parameters, such as improved flame control to prevent the flame from remaining on the fuel nozzle and swirler components. The inventors have been working on designing fuel nozzles and swirlers to meet the increased engine temperatures and durability requirements of hydrogen fuel.

[0033] Figure 1This is a schematic diagram of a turbine engine 10. As a non-limiting example, the turbine engine 10 can 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 rotatably connects the compressor section 12 and the turbine section 16 such that rotation of one affects rotation of the other, and defines the rotation axis 20 of the turbine engine 10.

[0034] Compressor section 12 may include a low-pressure (LP) compressor 22 and a high-pressure (HP) compressor 24 that are fluidly connected in series with each other. Turbine section 16 may include an HP turbine 26 and an LP turbine 28 that are fluidly connected in series with each other. Drive shaft 18 may operatively connect the LP compressor 22, HP compressor 24, HP turbine 26, and LP turbine 28 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.

[0035] 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. 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 turbine engine 10. It should be understood that the representation of compressor section 12 is merely illustrative and any number of blades, blades, and stages may be possible. Furthermore, it is contemplated that any number of other components may be present within compressor section 12.

[0036] 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. Turbine blades for one 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 turbine stages can be present, as the illustrated turbine section is merely schematic. Furthermore, it is contemplated that any number of other components may be present within turbine section 16.

[0037] 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.

[0038] During operation of the turbine engine 10, ambient air 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 to define pressurized air. This pressurized air can then flow into the combustion section 14, where it mixes with fuel and is ignited to generate combustion gases. The HP turbine 26 extracts some work from these combustion gases, driving the HP compressor 24. The combustion gases are discharged into the LP turbine 28, which extracts additional work to drive the LP compressor 22, and the exhaust gas is ultimately discharged from the turbine engine 10 via an exhaust section (not shown) downstream of the turbine section 16. The drive of the LP turbine 28 drives the LP spool to rotate the fan (not shown) and the LP compressor 22. The pressurized airflow and combustion gases together define the working airflow flowing through the fan, compressor section 12, combustion section 14, and turbine section 16 of the turbine engine 10.

[0039] Figure 2 Depicting along Figure 1The image shows a cross-sectional view of combustion section 14 along line II-II. Combustion section 14 may include a combustor 30, wherein annularly arranged fuel injectors 31 are disposed around the centerline or axis of rotation 20 of the turbine engine 10. It should be understood that the annularly arranged fuel injectors 31 may be one or more fuel injectors, and one or more of the fuel injectors 31 may have different characteristics. Depending on the type of engine in which the combustor 30 is located, the combustor 30 may have a canister-shaped, canister-annular, or annular arrangement. In a non-limiting example, the combustor 30 may have a combined arrangement positioned together with the engine housing 29.

[0040] The burner 30 may be at least partially defined by the burner liner 40. In some examples, the burner liner 40 may include an outer liner 41 and an inner liner 42 arranged concentrically with respect to each other and in an annular manner about the engine centerline or axis of rotation 20. In some examples, the burner liner 40 may have an annular structure with respect to the burner 30. In some examples, the burner liner 40 may include multiple segments or portions that together form the burner liner 40. The dome assembly 44, together with the burner liner 40, may at least partially define a combustion chamber 50 arranged annularly about the axis of rotation 20. The compressed air passage 32 may be at least partially defined by both the burner liner 40 and the housing 29.

[0041] Figure 3 Depicting along Figure 2 The cross-sectional view taken along line III-III shows combustion section 14. The burner 30 may include a fuel assembly 35 configured to supply fuel to the burner 30. The fuel assembly 35 may at least partially form a fuel injector 31. In some examples, the fuel assembly 35 may include annularly arranged fuel nozzles. It should be understood that such fuel nozzles may be organized in any suitable arrangement, pattern, grouping, etc.

[0042] The dome assembly 44 may include a dome wall 46 and a diffuser 48. The burner liner 40 and the dome assembly 44 may together define the combustion chamber 50 at least partially with respect to a longitudinal axis 52. The longitudinal axis 52 may extend between a forward direction 52F and a rearward direction 52A, as shown in the figure.

[0043] At least one fuel supply unit 54 may be fluidly connected to the combustion chamber 50 to supply fuel to the burner 30. In a non-limiting example, the fuel may include any suitable fuel, including hydrocarbon fuels, hydrogen fuels, or mixtures of different fuel types.

[0044] A fuel supply section 54 may be disposed within the dome assembly 44 to define a fuel outlet 58. It is contemplated that air may also be supplied or provided to the combustion chamber 50 via the fuel outlet 58. In this way, the fuel outlet 58 can provide a fuel-air mixture to the combustion chamber 50. Additionally, in some examples, multiple fuel injectors or premixers may be located on the dome wall 46. In some examples, multiple fuel injectors or premixers may be arranged in discrete clusters or groups on the dome wall 46.

[0045] In some examples, a flared cone 56 may be provided downstream of the fuel supply section 54. A swirler 60 may also be provided at the fuel assembly 35 to cause the incoming air to swirl near the fuel leaving the fuel supply section 54 and to provide a homogeneous mixture of air and fuel entering the burner 30.

[0046] A set of dilution orifices 62 may be provided in the burner liner 40 and configured to guide air into the combustion chamber 50 for temperature control, flame shaping, fuel-air mixing, etc. Any number of dilution orifices may be provided in the set of dilution orifices 62. The set of dilution orifices 62 may have any suitable pattern or arrangement on the burner liner 40, including straight rows, irregular groups, variable orifice diameters, etc., or combinations thereof. It is also contemplated that the burner 30 may be formed without any dilution orifices.

[0047] A fuel mixer 90 may also be disposed within the burner 30. The fuel mixer 90 may be configured to form a mixture of fuel and air and supply the mixture to the combustion chamber 50. Figure 4 In some examples, the fuel mixer 90 may include a housing 92 and a base 94. The fuel mixer 90 may also include at least one fuel nozzle assembly. In the illustrated example, at least one fuel nozzle assembly includes a first fuel nozzle assembly 100, a second fuel nozzle assembly 200, a third fuel nozzle assembly 300, and a fourth fuel nozzle assembly 400. Any number of fuel nozzle assemblies may be provided, including only one.

[0048] Referring to the first fuel nozzle assembly 100, as shown, the fuel nozzle assembly 100 may include a fuel nozzle 102 defining an upstream end 103 and a downstream end 105. At least one fuel nozzle assembly 100 may be carried, supported, or enclosed at the downstream end 105 by a housing 92. At least one fuel nozzle assembly 100 may also be coupled to a base 94 at the upstream end 103. The fuel nozzle assembly 100 may include a plate-like base member 107 at the upstream end 103. As shown, a mixture outlet 110 may also be located at the downstream end 105 of the fuel nozzle assembly 100.

[0049] The second, third, or fourth fuel nozzle assemblies 200, 300, and 400 may be similar to the first fuel nozzle assembly 100. Similar parts of the second, third, and fourth fuel nozzle assemblies 200, 300, and 400 will be identified herein by similar numbers incremented by 100, 200, and 300, respectively. It should be understood that the description of similar parts of fuel nozzle assembly 100 applies to fuel nozzle assemblies 200, 300, and 400 unless otherwise stated. It is contemplated that, in a non-limiting example, each of the first, second, third, and fourth fuel nozzle assemblies 100, 200, 300, and 400 may be coupled to the same base 94. It is also contemplated that the fuel mixer 90 may include any one or all of the first, second, third, or fourth fuel nozzle assemblies 100, 200, 300, and 400, with or without the housing 92 or base 94. Although the fuel mixer 90 is described as comprising four fuel nozzle assemblies with different configurations, it will be understood that the fuel mixer 90 may comprise multiple identical fuel nozzle assemblies, or fuel nozzle assemblies having a combination of features or aspects of the first, second, third, or fourth fuel nozzle assemblies 100, 200, 300, 400 described herein.

[0050] Figure 5 A cross-sectional view of a first fuel nozzle assembly 100 having a fuel nozzle 102 is shown. The fuel nozzle assembly 100 may include an outer wall 121 defining an interior. In some examples, a generally cylindrical member or tube may form the outer wall 121. In some examples, a central body 122 may include a cylindrical portion, a tapered portion, or a combination thereof. The outer wall 121 may at least partially surround the central body 122 circumferentially. In some examples, the outer wall 121 and the central body 122 may be concentrically aligned.

[0051] The central body 122 may also extend axially from the upstream end 103 of the fuel nozzle assembly 100 to the downstream end 105. The central body 122 may define a first longitudinal axis 124. The first longitudinal axis 124 may be aligned with the rotation axis 20. Figure 1 Coaxial, but not necessarily.

[0052] The annular body 129 can be disposed within the interior. As shown, the annular body 129 can divide its interior into a radially outer channel 138 and a radially inner channel 139. As shown, the central body 122 can be centrally disposed within the inner channel 139 of the annular body 129. In some examples, the central body 122 can be connected to the annular body 129 via a support 128.

[0053] The fuel supply channel 106 may also be located inside the annular body 129. The fuel supply channel 106 may have an annular arrangement, but it does not necessarily have to be. A set of fuel outlets 116 may be formed in the annular body 129 and fuel may be supplied from the fuel supply channel 106. The set of fuel outlets 116 may be radially arranged between the central body 122 and the outer wall 121. The fuel outlets 116 may be circumferentially spaced apart from each other.

[0054] The fuel supply passage 106 may define a second longitudinal axis 127. The second longitudinal axis 127 may be parallel to the first longitudinal axis 124, but it does not have to be.

[0055] A common flow channel 130 may be radially defined downstream of fuel outlet 116 between the central body 122 and the outer wall 121. In some examples, a set of fuel outlets 116 may be located upstream of the common flow channel 130. Each fuel outlet 116 may be fluidly connected at a corresponding upstream end 116a to a fuel supply channel 106 to supply a corresponding fuel flow 150 (indicated by an arrow). In some examples, the fuel supply channel 106 may be communicatively connected to a fuel source or fuel supply unit to receive fuel flow therefrom in a known manner, such as via a fuel pump. In some examples, the fuel supply channel 106 may define an annular shape. In some aspects, a portion of the fuel supply channel 106 may be substantially concentric with the central body 122.

[0056] Fuel outlet 116 may be further fluidly coupled to a common flow channel 130 at a corresponding downstream end 116b, and is configured to supply a corresponding fuel flow of received fuel to the common flow channel 130. In some examples, the downstream end 116b of fuel outlet 116 may include a corresponding nozzle or tip 117. Nozzle 117 may form an annular outlet. Fuel outlet 116 may include a corresponding tubular member 118 that fluidly couples a corresponding upstream end 116a to the downstream end 116b.

[0057] Fuel outlet 116 is arranged at the convergence of the first airflow 151 and the second airflow 152, injecting the corresponding fuel flow 150 into the common flow channel 130, thereby sandwiching the corresponding fuel flow 150 between the first airflow 151 and the second airflow 152. In some examples, the fuel flow 150 and the flame body (not shown) may be maintained radially inward of the outer wall 121 and the central body 122, or substantially centrally located within the common flow channel 130. These aspects can advantageously maintain low shear forces between the fuel and air, while keeping the fuel away from the lower flow velocity regions adjacent to the outer wall 121 and the central body 122. The reduction in shear forces reduces the shear layer deficiency between the airflow and the fuel flow. This reduction in deficiency provides an improved distribution of the radial velocity profile, which provides for maintaining high axial velocities for both the fuel and the airflow. High axial velocities can reduce or eliminate flame retention on the fuel nozzle 102, allowing the use of higher-temperature fuels, such as hydrogen fuel.

[0058] The annular body 129 may include a first annular wall 131 and a second annular wall 132. The first annular wall 131 may be radially disposed between the outer wall 121 and a set of fuel outlets 116. The second annular wall 132 may be radially disposed between the central body and the first annular wall 131. In some examples, the first annular wall 131 and the outer wall 121 may be concentrically aligned. The second annular wall 132 and the central body 122 may also be concentrically aligned.

[0059] The first compressed air flow passage 141 and the second compressed air flow passage 142 may also be disposed in the fuel nozzle 102. In some examples, the first compressed air flow passage 141 and the second compressed air flow passage 142 may be fluidly connected to a common compressed air source. In some examples, the first compressed air flow passage 141 may receive a separate air supply from the second compressed air flow passage 142.

[0060] A first compressed air flow passage 141 may be defined between an outer wall 121 and a first annular wall 131. In some examples, the first compressed air flow passage 141 may extend from the upstream end 103 of the fuel nozzle assembly 100 to a common flow passage 130. The first compressed air flow passage 141 may be in fluid communication with the common flow passage 130. The first compressed air flow passage 141 may be located radially outside a set of fuel outlets 116.

[0061] The second compressed air flow passage 142 may be defined between the second annular wall 132 and the central body 122. The second compressed air flow passage 142 may be disposed radially inside a set of fuel outlets 116. The second compressed air flow passage 142 may be in fluid communication with the common flow passage 130.

[0062] The first compressed air flow passage 141 and the second compressed air flow passage 142 may merge at the intersection 143. A common flow passage 130 may be fluidly connected to the intersection 143. The common flow passage 130 may also be fluidly connected to the fuel outlet 116. In this way, the intersection 143 may be fluidly connected to the fuel outlet 116.

[0063] In some examples, at least one first air inlet 133 may be provided. In the illustrated example, the first air inlet 133 is shown extending through the outer wall 121. It is also contemplated that, in non-limiting examples, at least one first air inlet 133 may be defined at the upstream end 103 of the fuel nozzle assembly 100, or through the base member 107, or through the outer wall 121, or a combination thereof. In some examples, a plurality of first air inlets 133 may be circumferentially spaced apart from each other. At least one first air inlet 133 may be in fluid communication with a first compressed air flow passage 141.

[0064] In some examples, at least one second air inlet 134 may be provided. In the illustrated example, the second air inlet 134 is shown extending through the base member 107. It is also contemplated that, in non-limiting examples, at least one second air inlet 134 may be defined at the upstream end 103 of the fuel nozzle assembly 100, or through the base member 107, or through the outer wall 121, or a combination thereof. In some examples, the second air inlets 134 may be circumferentially spaced from each other. The second air inlets 134 may be in fluid communication with the second compressed air flow passage 142.

[0065] A first airflow 151 (indicated by the dashed arrow) can be supplied to the first compressed air flow passage 141 through the first air inlet 133. For example, a specific first air inlet 133 defined through the upstream end of the outer wall 121 can radially deliver the first airflow 151 to the first compressed air flow passage 141. Alternatively, a specific first air inlet 133 defined through the base member 107 can axially deliver a corresponding first airflow 151 to the first compressed air flow passage 141. The first airflow 151 can then be delivered to the common flow passage 130 via the first compressed air flow passage 141.

[0066] A second airflow 152 (indicated by the dashed arrow) can be provided to the second compressed air flow passage 142 through at least one second air inlet 134. The second airflow 152 can be conveyed to the common flow passage 130 via the second compressed air flow passage 142. For example, a specific second air inlet 134 defined through the upstream end of the outer wall 121 can radially convey the corresponding second airflow 152 to the second compressed air flow passage 142. Alternatively, a specific second air inlet 134 defined through the base member 107 can axially convey the corresponding second airflow 152 to the second compressed air flow passage 142. The second airflow 152 can then be conveyed to the common flow passage 130 via the second compressed air flow passage 142. It is further contemplated that the first airflow 151 and the second airflow 152 can be arranged to converge adjacent to the fuel outlet 116.

[0067] A first compressed air flow passage 141 may define a first axial length L1. The first axial length L1 extends from a first air inlet 133 to a fuel outlet 116. It should be understood that the fuel outlet 116 may form the upstream end of a common flow passage 130. A second compressed air flow passage 142 may define a second axial length L2. The second axial length L2 extends from a second air inlet 134 to the fuel outlet 116. The first axial length L1 may be the same as or different from the second axial length L2. Furthermore, as shown, the common flow passage 130 may define a third axial length L3. As shown, the third axial length L3 extends from the fuel outlet 116 to the downstream end of the mixture outlet 110.

[0068] In some examples, the corresponding lengths of the first axial length L1 and the second axial length L2 can be determined to reduce turbulence, wake, or other non-uniformities present in the respective first airflows 151 and second airflows 152 received before mixing with the fuel flow 150. For example, the first axial length L1 of the common flow passage 130 can be determined to reduce or prevent backfire or flame persistence from the burner.

[0069] It is also anticipated that the common flow channel 130 may have a substantially constant cross-sectional area from upstream to downstream along the first axial length L3. The constant cross-sectional area of ​​the common flow channel 130 for the determined third axial length L3 can maintain the high speed of the fuel flow 150 to avoid backfire. The first axial length L1 and the second axial length L2 can be predetermined or selected to streamline the airflow upstream of the fuel outlet 116. It will be understood that streamlining the airflow can advantageously reduce or eliminate flow asymmetry, circumferential variations, and wake. Furthermore, the third axial length L3 can be predetermined to achieve a desired level of fuel-air mixing while avoiding flame holding or backfire.

[0070] Turning Figure 6 A schematic cross-sectional view of the fuel nozzle assembly 100 is shown. The mixture outlet 110 may define an outlet diameter (denoted as "D"), and the downstream end of the central body 122 may define an outer diameter (denoted as "d").

[0071] The first compressed air flow passage 141 and the second compressed air flow passage 142 can be arranged adjacent to the fuel outlet 116 and converge relative to each other. For example, the first compressed air flow passage 141 can define a first angle (denoted as "A1") relative to the second longitudinal axis 127. Similarly, the second compressed air flow passage 142 can define a second angle (denoted as "A2") relative to the second longitudinal axis 127. It is contemplated that the first angle A1 and the second angle A2 can each vary independently from 0 degrees to 90 degrees relative to the second longitudinal axis 127.

[0072] The common flow channel 130 may include an annular mixing section 130M and an annular output section 130P downstream of the mixing section 130M. The mixing section 130M may define an axial mixing length (denoted as "M"). The output section 130P may define an axial output length (denoted as "L4"). The annular mixing section 130M may be in fluid communication with the annular output section 130P.

[0073] In some examples, the common flow channel 130 may define a common flow channel height (denoted as "H") and a cross-sectional area 163. The cross-sectional area 163 may be constant or variable along the common flow channel 130. In one non-limiting example, the cross-sectional area 163 may converge from upstream to downstream along the axial mixing length M. In other non-limiting aspects, the cross-sectional area 163 along the axial mixing length M may diverge from upstream to downstream. In still other non-limiting aspects, the cross-sectional area 163 along the axial mixing length M may be constant from upstream to downstream. In some examples, the cross-sectional area 163 may vary by less than 20% along the axial mixing length M or the axial output length L4.

[0074] It is anticipated that the common flow channel height H at the downstream end 105 can be determined by one or both of the nozzle outlet diameter D and the outer diameter d of the center body. In one non-limiting example, the common flow channel height H can be determined as 50% of the difference between the nozzle outlet diameter D and the outer diameter d of the center body. In various non-limiting aspects, the ratio of the nozzle outlet diameter D to the outer diameter d of the center body can be adjusted or configured as needed, for example, depending on the desired target effective area at the mixture outlet 110. In some examples, the dimension of the axial output length L4 can be in the range of 10% to 40% of the common flow channel height H. For example, in some non-limiting aspects, the axial output length L4 can have a dimension between 5 mm and 20 mm. Alternatively or additionally, in some non-limiting aspects, the dimension of the axial output length L4 can be in the range of 0% to 25% of the axial mixing length M. For example, in some non-limiting aspects, the axial output length L4 can have a dimension between 0 mm and 20 mm.

[0075] Further anticipation is that, as shown in the figure, the first compressed air flow channel 141 may define a first cross-sectional area 161, and the second compressed air flow channel 142 may define a second cross-sectional area 162. In some examples, the second cross-sectional area 162 may be smaller than the first cross-sectional area 161. In this case, the flow velocity through the first compressed air flow channel 141 may be slower than the flow velocity through the second compressed air flow channel 142. In some examples, the first cross-sectional area 161 may have the same size as the second cross-sectional area 162. In some examples, one or both of the first cross-sectional area 161 or the second cross-sectional area 162 may vary or remain constant along the respective first compressed air flow channel 141 or second compressed air flow channel 142.

[0076] Figure 7-9 The fuel mixer 90 (shown according to the various aspects described herein) Figure 4 Some exemplary configurations of the fuel outlet used in ). Figure 7 A fuel outlet 116 of a first fuel nozzle assembly 100 in a first exemplary configuration is shown. A fuel supply passage 106, a first compressed air flow passage 141, a second air flow passage 142, and a common flow passage 130 are shown. A boss 117a may be provided surrounding the fuel outlet 116. The boss 117a may define a circular orifice 119 therethrough. The orifice 119 may be fluidly connected to a tubular member 118. A nozzle 117 having the orifice 119 may be oriented to directly supply a corresponding fuel flow 150 into the common flow passage 130 at an intersection 143.

[0077] Figure 8A fuel nozzle assembly 200 having a fuel outlet 216 in a second exemplary configuration is shown. Figure 4 The fuel nozzle assembly 200 includes a fuel supply passage 206, a nozzle 217, a first compressed air flow passage 241, a second air flow passage 242, and a common flow passage 230. As shown, the fuel outlet 216 may include a hollow sub-channel having an inlet 217b and a sub-channel outlet 217c. The sub-channel outlet 217c may be positioned upstream of the nozzle 217. In this way, the nozzle 217 can be configured to diffuse or disperse the fuel flow 250 within the fuel outlet 216 upstream of the intersection 243 and the common flow passage 230.

[0078] Figure 9 A fuel nozzle assembly 300 having a fuel outlet 116 in a third exemplary configuration is shown. Figure 4 The fuel nozzle assembly 300 includes a fuel supply passage 306, a nozzle 317, a first compressed air flow passage 341, a second air flow passage 342, and a common flow passage 330. In the illustrated example, the nozzle 317 is positioned at the downstream end of the first compressed air flow passage 341, upstream of the common flow passage 330. It is also contemplated that, in another non-limiting example, the nozzle 317 may be positioned at the downstream end of the second compressed air flow passage 342. In this way, the nozzle 317 may be oriented or configured such that the fuel flow 350 is mixed into one of the first compressed air flow passage 341 or the second compressed air flow passage 342 before being mixed with air from the other of the first compressed air flow passage 341 or the second compressed air flow passage 342 to form a first mixture flow. The first mixture flow may converge with air from the other of the first compressed air flow passage 341 or the second compressed air flow passage 342 to form a second mixture flow at the intersection 343.

[0079] Figure 10-11 The fuel mixer 90 (shown according to various aspects described herein) Figure 4 Some exemplary constructions of the outer wall used in ). Figure 10A second fuel nozzle assembly 200 is shown, having an outer wall 221, a central body 222, and a mixture outlet 210. In the illustrated example, the outer wall 221 may be oriented relative to the central body 222 to form a reduced cross-sectional area along a first axial length L1 within a common flow channel 230. This reduced cross-sectional area can form a converging common flow channel 230 in the direction toward the mixture outlet 210. In some examples, this converging common flow channel 230 can be arranged by converging the outer wall 221 while simultaneously holding the central body 222 into a cylindrical shape with a constant cross-sectional area. In operation, these aspects of the converging cross-sectional area of ​​the common flow channel 230 can advantageously enhance fuel-air mixing through the common flow channel 230.

[0080] Figure 11 A third fuel nozzle assembly 300 is shown, having an outer wall 321, a central body 322, and a mixture outlet 310. In the illustrated example, the outer wall 321 may be oriented relative to the central body 322 to form an increased cross-sectional area along a first axial length L1 within a common flow channel. This increased cross-sectional area can form a diverging common flow channel 330 in the direction toward the mixture outlet 310. In operation, the divergence of the common flow channel 330 allows fuel and air to be radially dispersed upstream and the fuel-air mixture to be radially guided outward along the common flow channel 330 to improve fuel-air mixing.

[0081] Figure 12-13 This generally illustrates the various aspects that can be achieved in the fuel mixer 90 (based on the aspects described herein). Figure 4 An exemplary construction of the air inlet used in ). Now refer to Figure 12 ,along Figure 4 The line CC shows the third fuel nozzle assembly 300 in cross-sectional view.

[0082] As shown in the figure, the third fuel nozzle assembly 300 may include a fuel nozzle 302 with a base member 307, an outer wall 321, a fuel outlet 316, a central body 322, an annular body 329, a common flow channel 330, first and second compressed air flow channels 341 and 342, a radially outer channel 338, a radially inner channel 339, at least one first air inlet 333, at least one second air inlet 334, and a mixture outlet 310. The first air flow 351 and the second air flow 352 are shown passing through the fuel nozzle assembly 300.

[0083] One difference compared to the fuel nozzle assembly 100 is that, as shown, each of the first air inlet 333 and the second air inlet 334 can be disposed in the base member 307. In this way, the first and second air inlets 333, 334 can axially deliver the corresponding first air flow 351 and second air flow 352 to the corresponding first and second compressed air flow channels 341, 342. As shown, the first and second air flows 351, 352 can also be delivered toward the mixture outlet 310 to the common flow channel 330.

[0084] Now for reference Figure 13 ,along Figure 4 The line DD shows the fourth fuel nozzle assembly 400 in cross-sectional view.

[0085] As shown in the figure, the fuel nozzle assembly 400 may include a fuel nozzle 402 with a base member 407, an outer wall 421, a fuel outlet 416, a central body 422, an annular body 429, a common flow channel 430, first and second compressed air flow channels 441 and 442, a radially outer channel 438, a radially inner channel 439, at least one first air inlet 433, at least one second air inlet 434, and a mixture outlet 410. A first airflow 451 and a second airflow 452 are shown passing through the fuel nozzle assembly 400.

[0086] One difference compared to the fuel nozzle assembly 100 is that, as shown, each of the first air inlet 433 and the second air inlet 434 can be disposed in the outer wall 421. In this way, the first and second air inlets 433, 434 can radially deliver a corresponding first air flow 451 and a second air flow 452 relative to the corresponding first and second compressed air flow channels 441, 442. As shown, the first and second air flows 451, 452 can also be delivered toward the mixture outlet 410 to the common flow channel 430.

[0087] Various aspects of this disclosure provide fuel nozzle assemblies having compressed air flow channels that define a common flow air circuit surrounding a set of fuel ports. The air circuit can be delivered to the common flow channel on radially opposite sides (e.g., radially inner and radially outer, respectively) of respective fuel flows from the set of fuel ports. The common flow air circuits can converge at the upstream end of the common flow channel. In some examples, the fuel flows can be injected into the common flow channel at the convergence or intersection of the common flow air flows, thereby sandwiching the fuel flows or forming stratified flows. In this way, the fuel flows and flame body can be maintained radially inner to or spaced apart from the outer and central bodies, or otherwise substantially centered within the common flow channel.

[0088] This disclosure further provides a method for mixing fuel in a combustor of a turbine engine. The method may include flowing a first compressed air stream, flowing a second compressed air stream, and converging the first and second compressed air streams at their intersection to form a converging air stream. The method may also include introducing fuel into at least one of the first compressed air stream, the second compressed air stream, or the converging air stream to form a mixture stream, and at least allowing the mixture stream to flow to the mixture outlet of a fuel mixer in the combustor. The method may also include introducing air into the converging air stream to form a mixture stream. The method may further include introducing air into a first compressed air stream upstream of the converging air stream to form a mixture stream.

[0089] 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.

[0090] Further aspects of the invention are provided by the subject matter of the following provisions:

[0091] A turbine engine includes: a compressor section, a combustion section, and a turbine section arranged in a series flow configuration, the combustion section having a combustor with a fuel mixer, the fuel mixer including: an outer wall defining a longitudinal direction and having a mixture outlet; a first compressed air flow passage and a second compressed air flow passage forming an intersection; a common flow passage fluidly connected to the intersection and the mixture outlet; and a fuel supply passage having a fuel outlet fluidly connected to at least one of the first compressed air flow passage, the second compressed air flow passage, or the intersection.

[0092] The turbine engine according to any one of the foregoing clauses further includes a central body located within the outer wall, and at least partially forming an annular profile for each of the first compressed air flow passage, the second compressed air flow passage, and the intersection between the central body and the outer wall.

[0093] In any of the preceding clauses, at least one of the fuel outlet or the mixture outlet of the turbine engine is annular.

[0094] The turbine engine according to any one of the foregoing clauses, wherein the common flow passage defines a mixing section and an outlet section, wherein the mixing section is adjacent to the fuel outlet, and the outlet section is adjacent to the mixture outlet.

[0095] The turbine engine according to any one of the foregoing clauses, wherein the common flow passage is defined within the mixing section with a cross-sectional area varying by less than 20%.

[0096] In any of the preceding clauses, the outer wall of the turbine engine forms an acute angle with the central body.

[0097] The turbine engine according to any one of the foregoing clauses, wherein the outer wall and the central body form one of a converging cross-sectional area or a diverging cross-sectional area in a downstream direction through the outlet portion.

[0098] The turbine engine according to any one of the foregoing clauses, wherein the first compressed air flow passage includes a first cross-sectional area, and the second compressed air flow passage includes a second cross-sectional area, the second cross-sectional area being different from the first cross-sectional area upstream of the intersection.

[0099] The turbine engine according to any one of the foregoing clauses, wherein the fuel outlet is fluidly connected to the intersection.

[0100] The turbine engine according to any one of the foregoing clauses, wherein the fuel outlet is fluidly connected to the first compressed air flow passage upstream of the intersection.

[0101] The turbine engine according to any one of the foregoing clauses, wherein the fuel outlet includes a hollow sub-channel having a sub-channel outlet upstream of the intersection.

[0102] The turbine engine according to any one of the foregoing clauses, wherein the first compressed air flow passage defines a first angle relative to the fuel supply passage, and the second compressed air flow passage defines a second angle relative to the fuel supply passage, wherein the first angle is different from the second angle.

[0103] The turbine engine according to any one of the foregoing clauses, wherein the first angle is greater than the second angle.

[0104] The turbine engine according to any one of the foregoing clauses, wherein the first compressed air flow passage includes a first inlet, and the second compressed air flow passage includes a second inlet, wherein at least one of the first inlet or the second inlet is oriented to provide compressed air in a direction parallel to or perpendicular to the longitudinal direction.

[0105] The turbine engine according to any one of the foregoing clauses, wherein at least one of the first inlet or the second inlet is located in the outer wall.

[0106] A combustor for a turbine engine includes: a combustor liner that at least partially defines a combustion chamber; and a fuel mixer fluidly connected to the combustion chamber, the fuel mixer including: an outer wall defining a longitudinal direction and having a mixture outlet; a first compressed air flow passage and a second compressed air flow passage forming an intersection; a common flow passage fluidly connected to the intersection and the mixture outlet; and a fuel supply passage having a fuel outlet fluidly connected to at least one of the first compressed air flow passage, the second compressed air flow passage, or the intersection.

[0107] The burner according to any one of the foregoing clauses further includes a central body located within the outer wall, and at least partially forming an annular profile for each of the first compressed air flow passage, the second compressed air flow passage, and the intersection between the central body and the outer wall.

[0108] In any of the preceding clauses, at least one of the fuel outlet or the mixture outlet is annular.

[0109] According to any one of the foregoing clauses, the common flow passage defines a mixing section and an outlet section, wherein the mixing section is adjacent to the fuel outlet and the outlet section is adjacent to the mixture outlet.

[0110] In any of the preceding clauses, the common flow channel is defined within the mixing section with a cross-sectional area varying by less than 20%.

[0111] In any of the preceding clauses, the outer wall of the burner forms an acute angle with the central body.

[0112] In any of the preceding clauses, the outer wall and the central body form one of a converging cross-sectional area or a diverging cross-sectional area in the downstream direction through the outlet portion of the burner.

[0113] According to any one of the foregoing clauses, the first compressed air flow passage includes a first cross-sectional area, and the second compressed air flow passage includes a second cross-sectional area, the second cross-sectional area being different from the first cross-sectional area upstream of the intersection.

[0114] The burner according to any one of the foregoing clauses, wherein the fuel outlet is fluidly connected to the intersection.

[0115] According to any one of the preceding clauses, the burner wherein the fuel outlet is fluidly connected to the first compressed air flow passage upstream of the intersection.

[0116] The burner according to any one of the foregoing clauses, wherein the fuel outlet includes a hollow sub-channel having a sub-channel outlet upstream of the intersection.

[0117] According to any one of the preceding clauses, the first compressed air flow passage defines a first angle relative to the fuel supply passage, and the second compressed air flow passage defines a second angle relative to the fuel supply passage, wherein the first angle is different from the second angle.

[0118] The burner according to any one of the foregoing clauses, wherein the first angle is greater than the second angle.

[0119] According to any one of the foregoing clauses, the first compressed air flow passage includes a first inlet, and the second compressed air flow passage includes a second inlet, wherein at least one of the first inlet or the second inlet is oriented to provide compressed air in a direction parallel to or perpendicular to the longitudinal direction.

[0120] In any of the preceding clauses, at least one of the first inlet or the second inlet is located in the outer wall of the burner.

[0121] A method for mixing fuel in a combustor of a turbine engine, the method comprising: flowing a first compressed air stream; flowing a second compressed air stream; converging the first compressed air stream and the second compressed air stream at an intersection to form a converging air stream; introducing fuel into at least one of the first compressed air stream, the second compressed air stream, or the converging air stream to form a mixture stream; and at least flowing the mixture stream to a mixture outlet of a fuel mixer in the combustor.

[0122] The method according to any one of the foregoing clauses, wherein introducing fuel includes introducing fuel into the converging air stream to form the mixture stream.

[0123] The method according to any one of the foregoing clauses, wherein introducing fuel further comprises introducing fuel between the first compressed air stream and the second compressed air stream to form the mixture stream as a stratified stream.

[0124] The method according to any one of the foregoing clauses further includes introducing fuel into the first compressed air flow upstream of the intersection to form the mixture flow, and converging the mixture flow with the second compressed air flow at the intersection to form a second mixture flow.

Claims

1. A turbine engine, characterized in that, include: A compressor section, a combustion section, and a turbine section are arranged in a series flow configuration. The combustion section has a combustor with a fuel mixer that receives a hydrogen fuel stream, and the fuel mixer includes: An outer wall defining the longitudinal direction and having a mixture outlet; the outer wall is arranged in a ring shape; A base member, the base member being partially located in front of the outer wall and extending into the interior of the outer wall, the base member having an annular outer wall and an annular inner wall; A first compressed air flow channel is defined between the annular outer wall and the outer wall of the base member, and the first compressed air flow channel has a first air inlet disposed on the outer wall and receiving a first air flow. A second compressed air flow channel is defined between the annular inner wall of the base member and the central body. The second compressed air flow channel has a second air inlet for receiving a second airflow. The first compressed air flow channel and the second compressed air flow channel form an intersection. The central body is disposed inside the first compressed air flow channel and the second compressed air flow channel. A common flow channel extending from the intersection to the mixture outlet and at least partially defined by the central body, and A fuel supply channel having a fuel outlet fluidly connected to the intersection, and the fuel outlet being arranged to inject a hydrogen fuel stream as a sandwich between the first air stream and the second air stream.

2. The turbine engine according to claim 1, characterized in that, The common flow channel defines a mixing section with a converging cross-sectional area and an outlet section with a constant cross-sectional area, wherein the mixing section is adjacent to the fuel outlet and the outlet section is adjacent to the mixture outlet.

3. The turbine engine according to claim 2, characterized in that, The common flow channel is defined within the mixing section with a cross-sectional area that varies by less than 20%.

4. The turbine engine according to claim 2, characterized in that, The mixing section defines an axial mixing length, and the outlet section defines an axial output length, wherein the axial output length is between 0 and 25% of the axial mixing length.

5. The turbine engine according to claim 2, characterized in that, The outlet portion of the common flow channel defines the height of the common flow channel at the mixture outlet, and also defines the axial output length between the mixing portion and the mixture outlet, wherein the axial output length is between 10% and 40% of the height of the common flow channel.

6. The turbine engine according to claim 1, characterized in that, The first compressed air flow channel includes a first cross-sectional area, and the second compressed air flow channel includes a second cross-sectional area, the second cross-sectional area being different from the first cross-sectional area upstream of the intersection.

7. The turbine engine according to claim 1, characterized in that, The fuel outlet includes a hollow sub-channel, which has a sub-channel outlet upstream of the intersection.

8. The turbine engine according to claim 1, characterized in that, The first compressed air flow passage defines a first angle relative to the fuel supply passage, and the second compressed air flow passage defines a second angle relative to the fuel supply passage, wherein the first angle is different from the second angle.

9. The turbine engine according to claim 1, characterized in that, At least one of the first air inlet or the second air inlet is oriented to provide compressed air in a direction parallel to or perpendicular to the longitudinal direction.

10. The turbine engine according to claim 9, characterized in that, At least one of the first air inlet or the second air inlet is located in the outer wall.

11. The turbine engine according to claim 1, characterized in that, The common flow channel defines a common flow channel height, the mixture outlet defines an outlet diameter, and the central body defines an outer diameter, wherein the common flow channel height is 50% of the difference between the outlet diameter and the outer diameter of the central body.

12. The turbine engine according to claim 1, characterized in that, The first air inlet is defined between the outer wall and the base member located in front of the outer wall, and is configured to provide the first airflow to the first compressed airflow passage.

13. A combustor for a turbine engine, characterized in that, include: The burner liner that at least partially defines the combustion chamber; and A fuel mixer that receives hydrogen fuel and is fluidly coupled to the combustion chamber, the fuel mixer comprising: An outer wall defining the longitudinal direction and having a mixture outlet; A base member, the base member being partially located in front of and extending into the interior of the outer wall, and the base member having an annular outer wall and an annular inner wall; and defining a first compressed air flow channel between the annular outer wall and the outer wall of the base member, the first compressed air flow channel receiving a first airflow; A first air inlet is located between the outer wall and the base member and is configured to provide the first airflow to the first compressed airflow channel; A second compressed air flow channel is located between the annular inner wall and the central body of the base member. The second compressed air flow channel has a second air inlet for receiving a second airflow, and the first compressed air flow channel and the second compressed air flow channel form an intersection. The central body is disposed inside the first compressed air flow channel and the second compressed air flow channel. A common flow channel extending from the fluid at the intersection to the outlet of the mixture, and A fuel supply channel having a fuel outlet fluidly connected to the intersection, and the fuel outlet being arranged to inject a hydrogen fuel stream as a sandwich between the first air stream and the second air stream.

14. The burner according to claim 13, characterized in that, The common flow channel defines a mixing section and an outlet section, wherein the mixing section is adjacent to the fuel outlet and the outlet section is adjacent to the mixture outlet, and wherein the common flow channel is further defined within the mixing section with a cross-sectional area varying by less than 20%.

15. The burner according to claim 13, characterized in that, The fuel outlet includes a hollow sub-channel, which has a sub-channel outlet upstream of the intersection.

16. A method for mixing fuel in the combustor of a turbine engine, characterized in that, The method includes: A first compressed air flow is directed to a first compressed air flow channel located between an outer wall and a base member, the first compressed air flow channel receiving the first compressed air flow from a first air inlet located between the outer wall and the base member; wherein the base member is partially located in front of the outer wall and extends into the interior of the outer wall, the base member having an annular outer wall and an annular inner wall, and the first compressed air flow channel is defined between the annular outer wall and the outer wall of the base member; The second compressed air flow is directed to a second compressed air flow channel; wherein the second compressed air flow channel is defined between the annular inner wall of the base member and the central body, the second compressed air flow channel has a second air inlet for receiving the second compressed air flow, and the central body is located inside the first compressed air flow channel and the second compressed air flow channel; The first compressed air flow and the second compressed air flow converge at the intersection. At the intersection, an annular hydrogen fuel is introduced between the first and second compressed air flows to form a stratified mixture flow; and At least the mixture flow should be directed to the mixture outlet of the fuel mixer of the burner.

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