Combustor fuel assembly

Abstract

A turbine engine can include a compressor section, a combustion section, and a turbine section in an axial flow arrangement. The combustion section can include a combustor having a fuel-air mixer. The fuel-air mixer can include a body having at least one air passage and a set of mixing passages.

Description

[0001] Cross-references to related applications

[0002] This application claims the benefit of U.S. Provisional Application No. 63 / 311,657, filed February 18, 2022, and U.S. Patent Application No. 17 / 734,469, filed May 2, 2022, the entire contents of which are incorporated herein by reference. Technical Field

[0003] This topic generally relates to combustors with fuel assemblies for turbine engines, and more specifically to fuel assemblies with fuel-air mixing arrangements. Background Technology

[0004] A turbine engine is driven by a flow of combustion gases through the engine, which rotates multiple turbine blades. These turbine blades, in turn, rotate a compressor to supply compressed air to a combustor for combustion. The combustor can be located within the turbine engine and fluidly connected to the turbine through which the combustion gases flow.

[0005] The use of hydrocarbon fuels in the combustors of turbine engines is known. Generally, air and fuel are supplied to the combustion chamber, mixed, and then the fuel burns in the presence of air to produce hot gases. These hot gases are then supplied to the turbine, where they are cooled and expand to generate power. Byproducts of fuel combustion typically include environmentally harmful byproducts such as nitrogen oxides and nitrogen dioxide (collectively known as NO). x ), CO, UHC (e.g., methane and volatile organic compounds that contribute to the formation of atmospheric ozone), and other oxides including sulfur oxides (e.g., SO2 and SO3).

[0006] Various fuels are being explored for use in gas turbine engines. Hydrogen, or hydrogen mixed with another element or compound, can be used for combustion, but hydrogen or hydrogen blends can result in higher flame temperatures than conventional fuels. That is, hydrogen or hydrogen blends typically have a wider combustible range and faster combustion rates than conventional fuels such as petroleum-based fuels or blends of petroleum and synthetic fuels.

[0007] Standards governing air pollution problems worldwide regulate nitrogen oxides (NOx) generated by turbine engine operation. x Emissions include unburned hydrocarbons (UHC) and carbon monoxide (CO). In particular, due to the high burner flame temperature during operation, nitrogen oxides (NOx) can form within the burner. x The desired effect is to reduce NO by adjusting the contours or patterns within the burner. x Emissions can be reduced while maintaining the desired efficiency. Attached Figure Description

[0008] In the drawings:

[0009] Figure 1 is a schematic illustration of a turbine engine having a compression section, a combustion section, and a turbine section, in accordance with various aspects described herein.

[0010] Figure 2 is a schematic illustration of a turbine engine having a compression section, a combustion section, and a turbine section, in accordance with various aspects described herein. Figure 1 is a cross-sectional view of the combustion section of

[0011] Figure 3 is a cross-sectional view of the combustion section of Figure 2 Figure 2 is a cross-sectional view of the combustor of the combustion section of

[0012] Figure 4 is a cross-sectional view of the combustor of the combustion section of Figure 3

[0013] Figure 5 is a front view of the fuel-air mixer of Figure 4

[0014] Figure 6 is a side cross-sectional view of the fuel-air mixer of Figure 4 Figure 5

[0015] Figure 7 Figure 4 is a side cross-sectional view of the fuel-air mixer of Figure 5

[0016] Figure 8 is a front cross-sectional view of the fuel-air mixer of Figure 4 Figure 7

[0017] Figure 9 is a side cross-sectional view of another fuel-air mixer that can be used in the combustor of Figure 3

[0018] Figure 10 is a front view of the fuel-air mixer of Figure 9

[0019] Figure 11 is a front cross-sectional view of the fuel-air mixer of Figure 9 Figure 9

[0020] ​​​​​​​​​​​​​Figure 12 Based on the various aspects described in this article, it is possible to... Figure 3 A side cross-sectional view of another fuel-air mixer used in a burner.

[0021] Figure 13 yes Figure 12 Front view of the fuel-air mixer.

[0022] Figure 14 yes Figure 12 fuel-air mixer along Figure 12 Front cross-sectional view of line XIV-XIV.

[0023] Figure 15 Based on the various aspects described in this article, it is possible to... Figure 3 A side cross-sectional view of another fuel-air mixer used in a burner.

[0024] Figure 16 yes Figure 15 Front view of the fuel-air mixer.

[0025] Figure 17 yes Figure 15 fuel-air mixer along Figure 15 Front cross-sectional view of line XVII-XVII. Detailed Implementation

[0026] The aspects of the disclosure described herein relate to combustors with fuel nozzle assemblies. For illustrative purposes, this disclosure will be described in relation to turbine engines. However, it will be understood that the aspects of the disclosure described herein are not limited thereto, and the combustor described herein can be implemented in engines, including but not limited to turbojet engines, turboprop engines, turboshaft engines, and turbofan engines. The aspects of the disclosure discussed herein are generally applicable to non-aircraft engines with combustors, such as in other mobile applications and non-mobile industrial, commercial, and residential applications.

[0027] 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.

[0028] 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.

[0029] The terms "forward" and "aft" refer to relative positions within a gas turbine engine or vehicle and refer to the normal operating attitude of the gas turbine engine or vehicle. For example, for a gas turbine engine, forward refers to a position closer to the engine inlet and aft refers to a position closer to the engine nozzle or exhaust.

[0030] As used herein, the term "upstream" refers to a direction opposite to the direction of fluid flow, while the term "downstream" refers to a direction the same as the direction of fluid flow. The terms "forward" or "forwardly" mean in front of something, and "rearward" or "rearwardly" mean behind something. For example, when used in relation to fluid flow, forward / downstream can mean upstream, and rearward / aft can mean downstream.

[0031] The term "fluid" can be a gas or a liquid. The term "fluid communication" means that a fluid is able to establish a connection between designated areas.

[0032] Further, as used herein, the term "radial" or "radially" refers to a direction away from a common center. For example, in the overall context of a turbine engine, radial refers to a direction along a ray extending between a central longitudinal axis of the engine and an outer periphery of the engine.

[0033] All directional references (e.g., radial, axial, proximal, distal, upper, lower, upward, downward, left, right, lateral, front, back, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, aft, etc.) are only used for identification purposes to aid the reader's understanding of the present disclosure, and do not create limitations, particularly as to the position, orientation, or use of the disclosure described herein. Connection references (e.g., attached, coupled, connected, and joined) are to be construed broadly and will be given their ordinary and accustomed meaning to those skilled in the art unless otherwise explicitly provided. As such, connection references do not necessarily imply that two elements are directly connected to each other without intervening structures or media. The exemplary drawings are for purposes of example only and the dimensions, positions, order and relative sizes reflected in the attached drawings attached hereto can vary.

[0034] The singular forms "a," "an," and "the" include plural references unless the context clearly dictates otherwise. Further, as used herein, the term "set" or "a set" of elements can be any number of elements, including only one.

[0035] Approximating language, as used herein throughout the specification and claims, is applied to modify any quantitative representation that could permissibly vary without resulting in a change of the basic function to which it is directed. Accordingly, a value modified by a term or terms, such as "about", "approximately”, “substantially”, and “essentially”, is not limited to the precise value specified. In at least some instances, the approximating language can correspond to the precision of an instrument for measuring the value or the precision of the method or machine for constructing or manufacturing the item and / or system providing the value. In at least some instances, the approximating language can correspond to the precision of an instrument for measuring the value or the precision of the method or machine for constructing or manufacturing the item and / or system providing the value. For example, the approximating language can refer to being within 1%, 2%, 4%, 5%, 10%, 15%, or 20% of the stated value. Here and throughout the specification and claims, range limitations are combined and interchanged, such ranges are identified and include all the sub-ranges contained therein, unless context or language indicates otherwise. For example, all ranges disclosed herein are inclusive of the endpoints, and endpoints are independently combinable with each other.

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

[0037] The compressor section 12 can include a low pressure (LP) compressor 22 and a high pressure (HP) compressor 24 fluidly coupled in series with one another. The turbine section 16 can include a HP turbine 26 and a LP turbine 28 fluidly coupled in series with one another. The drive shaft 18 can 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 can include a LP drive shaft (not shown) and a HP drive shaft (not shown). The LP drive shaft can couple the LP compressor 22 to the LP turbine 28, and the HP drive shaft can couple the HP compressor 24 to the HP turbine 26. A LP train can be defined as a combination of the LP compressor 22, the LP turbine 28, and the LP drive shaft such that rotation of the LP turbine 28 can impart a driving force to the LP drive shaft, which in turn can cause the LP compressor 22 to rotate. A HP train can be defined as a combination of the HP compressor 24, the HP turbine 26, and the HP drive shaft such that rotation of the HP turbine 26 can impart a driving force to the HP drive shaft, which in turn can cause the HP compressor 24 to rotate.

[0038] The compressor section 12 can include a plurality of axially spaced stages. Each stage includes a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary vanes. The compressor blades for a stage of the compressor section 12 can be mounted to a disk, which is mounted to the drive shaft 18. Each set of blades for a given stage can have its own disk. The vanes of the compressor section 12 can be mounted to a casing, which can extend circumferentially around the turbine engine 10. It should be appreciated that the representation of the compressor section 12 is merely illustrative and there can be any number of blades, vanes, and stages. Further, it is contemplated that there can be any number of other components within the compressor section 12.

[0039] Similar to the compressor section 12, the turbine section 16 can include a plurality of axially spaced stages, with each stage having a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary vanes. The turbine blades for a stage of the turbine section 16 can be mounted to a disk, which is mounted to the drive shaft 18. Each set of blades for a given stage can have its own disk. The vanes of the turbine section 16 can be mounted to a casing in a circumferential manner. It is noted that there can be any number of blades, vanes, and turbine stages, as the illustrated turbine section 16 is merely a representative illustration. Further, it is contemplated that there can be any number of other components within the turbine section 16.

[0040] The combustion section 14 can be serially disposed between the compressor section 12 and the turbine section 16. The combustion section 14 can be fluidly coupled to at least a portion of the compressor section 12 and the turbine section 16, such that the combustion section 14 at least partially fluidly couples the compressor section 12 to the turbine section 16. As a non-limiting example, the combustion section 14 can be fluidly coupled to the HP compressor 24 at an upstream end of the combustion section 14 and fluidly coupled to the HP turbine 26 at a downstream end of the combustion section 14.

[0041] 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.

[0042] Figure 2 Depicting along Figure 1 The image shows a cross-sectional view of combustion section 14 along line II-II. Combustion section 14 may include a burner 30 having an annular arrangement of fuel injectors 31 arranged around the centerline or axis of rotation 20 of the turbine engine 10. It should be understood that the annular fuel injectors 31 may be one or more fuel injectors, and one or more of the fuel injectors 31 may have different characteristics. In some examples, multiple fuel injectors 31 may be positioned in a cluster arrangement, such as a single fuel injector or cup with multiple premixer tubes. Depending on the type of engine in which the burner 30 is located, the burner 30 may have a canister, canister annular, or annular arrangement. In a non-limiting example, the burner 30 may have a combined arrangement positioned together with the housing 29 of the engine 10.

[0043] The burner 30 may be at least partially defined by the burner bushing 40. In some examples, the burner bushing 40 may include an outer bushing 41 and an inner bushing 42, which are concentric with respect to each other and arranged in an annular manner around the engine centerline or axis of rotation 20. In some examples, the burner bushing 40 may have an annular structure around the burner 30. In some examples, the burner bushing 40 may include multiple segments or portions that together form the burner bushing 40. The dome assembly 44, together with the burner bushing 40, may at least partially define a combustion chamber 50, which is arranged annularly around the engine centerline or axis of rotation 20. The compressed air passage 32 may be at least partially defined by both the burner bushing 40 and the housing 29.

[0044] Figure 3 Depicting along Figure 2The cross-sectional view taken along line III-III shows the burner 30. The burner 30 may include a fuel assembly having a fuel-air mixer 35 configured to supply fuel to the burner 30. The fuel-air mixer 35 may at least partially form a fuel injector 31. In some examples, the fuel-air mixer 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.

[0045] The dome assembly 44 may include a dome wall 46 and a diffuser 48. The burner bushing 40 and the dome assembly 44 may together define the combustion chamber 50 at least partially around a longitudinal axis 52. As shown, the longitudinal axis 52 may extend between a forward direction 52F and a rearward direction 52A.

[0046] At least one fuel supply 54 may be fluidly connected to the combustion chamber 50 to supply fuel to the burner 30. Although only one fuel supply 54 is shown, multiple fuel supplies may be provided, and they may supply the same or different fuels. In a non-limiting example, the fuel may include any suitable fuel, including hydrocarbon fuels, hydrogen fuels, or mixtures of different fuel types.

[0047] A fuel supply 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. In some examples, a flared cone 56 may be disposed downstream of the fuel supply 54. A swirler 60 may also be disposed at the fuel-air mixer 35 to cause the incoming air to swirl near the fuel exiting the fuel supply 54 and to provide a homogeneous mixture of air and fuel entering the combustor 30. It is also contemplated that the swirler 60 may be integrated into the fuel-air mixer 35.

[0048] A set of dilution orifices 62 may be provided in the burner bushing 40 and configured to guide air into the combustion chamber 50 for temperature control, flame shaping, fuel-air mixing, etc. In the illustrated example, a set of dilution orifices 62 is provided in both the outer bushing 41 and the inner bushing 42, but this is not mandatory. Any number of dilution orifices may be provided in this set of dilution orifices 62. The set of dilution orifices 62 may have any suitable pattern or arrangement on the burner bushing 40, including linear rows, irregular groups, variable orifice sizes, etc., or combinations thereof. It is further envisioned that the burner 30 may be formed without any dilution orifices. In some examples, one or more lean premixers may be provided in or near the dome assembly 44.

[0049] Turn Figure 4In one exemplary embodiment, a side view of a fuel-air mixer 35 is shown. The fuel-air mixer 35 can be configured to form multiple fuel and air streams into a combustion chamber 50. Figure 3 In this process, multiple fuel streams can be adjusted according to combustion requirements. For example, multiple fuel streams can supply mixtures of different types and / or the same or different fuel types. As shown, the fuel-air mixer 35 may include a body 70 having a central axis C. In some examples, the central axis C may be aligned with the longitudinal axis 52. Figure 3 Alignment. Body 70 may include a first portion 70A and a second portion 70B. In some examples, the first portion 70A may include, or at least partially form, the fuel outlet 58.

[0050] The body 70 may include an outer wall 71 and a set of inlets 71A within the outer wall 71. The set of inlets 71A may have any number, pattern, shape, or arrangement of inlets. In the example shown, the set of inlets 71A includes discrete, axially spaced inlets or orifices configured to guide air into the interior of the body 70 for mixing with fuel therein. The set of inlets 71A allows compressed air to flow from the compressor section 12 (… Figure 1 ) flows into the fuel-air mixer 35.

[0051] Figure 5 A front view of the fuel-air mixer 35 is shown, in which the first portion 70A is visible. In some examples, the first portion 70A may include a dome wall 46, but this is not necessarily the case.

[0052] The fuel-air mixer 35 may include one or more outlets, forming a set of outlets 78. Although six outlets are shown in the set of outlets 78, any number can be provided. As shown, the set of outlets 78 may collectively form a fuel outlet 58. The set of outlets 78 may have any suitable pattern or arrangement, including linear rows, annular groupings, multiple concentric circles, irregular groupings, etc., or combinations thereof. In some examples, the set of outlets 78 may be configured to swirl the fuel or air leaving the body 70. In some examples, the set of outlets 78 may also be configured to discharge fuel or air from the body 70 in a jet or other generally linear manner.

[0053] The body 70 may also include multiple inner walls and orifices forming corresponding multiple internal channels, which are configured to guide or mix air and fuel upstream of the fuel outlet 58. Figure 5 A set of outlets 78 in the diagram shows portions of these walls, openings, and passages. For example, in the view shown, portions of a set of inlets 71A are visible through this set of outlets 78.

[0054] Now for reference Figure 6VI-VI along the line Figure 5 A cross-sectional view of the fuel-air mixer 35 is shown. The body 70 is illustrated as having a first portion 70A and a second portion 70B as shown.

[0055] In the illustrated example, the body 70 may further include an inner wall 72, which is located radially inside the outer wall 71 relative to the central axis C. A set of internal orifices 72A may be provided in the inner wall 72. The body 70 may also include a third wall 73 and a fourth wall 74, each having a third set of orifices 73A and a fourth set of orifices 74A, respectively.

[0056] The body 70 may further include a central wall 76 extending along the central axis C, as shown in the figure. The central wall 76 may be in the form of a hollow wall. The central wall 76 may be located radially inside the inner wall 72. As shown in the figure, the central wall 76 may also include a set of central orifices 76A.

[0057] Any of the outer wall 71, inner wall 72, third wall 73, or fourth wall 74 may extend at least partially along the central axis C, or may extend at least radially relative to the central axis C, or a combination thereof. In some examples, two or more of the outer wall 71, inner wall 72, third wall 73, or fourth wall 74 may be part of a common wall within the body 70.

[0058] In the non-limiting example shown, body 70 may include a set of mixing channels 81, a second set of channels 82, a central fuel channel 85, a central air channel 86, and a set of outlet mixing channels 88. A central wall 76 may at least partially form the central fuel channel 85. In some examples, the central wall 76 may separate the central fuel channel 85 and the central air channel 86. The central air channel 86 may at least partially surround the central fuel channel 85.

[0059] A set of inlets 71A can be fluidly connected to a set of mixing channels 81. A third set of orifices 73A can be fluidly connected to a set of mixing channels 81 and a second set of channels 82. A set of internal orifices 72A can be fluidly connected to a central air channel 86 and a set of mixing channels 81. A set of outlet mixing channels 88 can be fluidly connected to at least one of a set of mixing channels 81 or a central air channel 86 through a fourth set of orifices 74A.

[0060] The set of outlet mixing channels 88 can be arranged in a ring around the central axis C, such that portions of multiple channels in the set of outlet mixing channels 88 are shown in the view shown. Furthermore, in the example shown, a set of central orifices 76A can fluidly connect the central fuel channel 85 and the set of outlet mixing channels 88.

[0061] Furthermore, a set of central orifices 76A can be formed at the inlet of a set of outlet mixing channels 88 and can have a corresponding angle 87 relative to the central axis C. In some non-limiting examples, the angle 87 can be between 1-179 degrees, or between 10-150 degrees, or between 20-120 degrees, etc. Any suitable angle 87 can be set. In this way, the set of central orifices 76A can form discrete fuel ports that are fluidly connected to the set of outlet mixing channels 88 downstream of the set of mixing channels 81. It is conceivable that the set of central orifices 76A can also include staggered or varying axial or circumferential positions relative to the central axis C. In the non-limiting example shown, the set of central orifices 76A can be located behind a set of inner orifices 72A. In this way, the mixing length can vary in the circumferential direction around the fuel-air mixer 35 for different fuel flows.

[0062] Each of the outlets 78 in the set can also define an outlet direction 100, forming an outlet angle 101 relative to the central axis C. In some non-limiting examples, the outlet angle 101 can be between -80 degrees and +80 degrees, or between -60 degrees and +60 degrees, or between -20 degrees and +20 degrees, etc., or combinations thereof. Further envisioning is that the set of outlets 78 can have the same or different outlet angles 101.

[0063] Multiple flow paths can be formed through multiple internal channels of the body 70. In the non-limiting example shown, a first fuel flow path 91 can sequentially extend from a second set of channels 82 to a set of mixing channels 81 and then to a set of outlet mixing channels 88. A second fuel flow path 92 can extend from a central fuel channel 85 to a set of outlet mixing channels 88. An inlet flow path 93 can extend through a set of inlets 71A and into a set of mixing channels 81. A central air flow path 94 can extend along a central air channel 86 and into a set of mixing channels 81. In this way, multiple axially staggered flow paths can be arranged in the fuel-air mixer 35.

[0064] In one exemplary embodiment, during operation, air may be supplied to the body 70 along at least one of an inlet flow path 93 or a central air flow path 94, and fuel may be supplied along at least one of a first fuel flow path 91 or a second fuel flow path 92. For example, air supplied along the central air passage 86 may be directed or diverted to a set of mixing passages 81 and mixed with fuel entering the set of mixing passages 81 from a second set of passages 82. Air may also enter the set of mixing passages 81 through a set of inlets 71A and mix with fuel or air therein. In this way, a first fuel-air mixture may be formed within the set of mixing passages 81. The first fuel-air mixture may enter a set of outlet mixing passages 88 through a fourth set of orifices 74A.

[0065] Additional fuel supplied along the central fuel passage 85 can also be guided through a set of central orifices 76A into a set of outlet mixing passages 88. Such fuel encounters the first fuel-air mixture supplied from the set of mixing passages 81 and forms a second fuel-air mixture or enriched fuel-air mixture within the set of outlet mixing passages 88 exiting the body 70. In this way, fuel and air can be premixed at multiple axial locations upstream of the set of outlets 78 within the body 70. Although described as supplying fuel or air, it should be understood that air, fuel, or a mixture of air and fuel can be supplied through any or all of the first fuel flow path 91, the second fuel flow path 92, the inlet flow path 93, or the central air flow path 94. Air, fuel, or a mixture thereof can be combined within the set of mixing passages 81 or the set of outlet mixing passages 88. Such a mixture can be guided through the set of outlet mixing passages 88 and supplied through the fuel outlet 58 for combustion in the combustion chamber 50. Figure 3 It burns inside the body.

[0066] In some examples, the fuel-air mixer 35 may include 100% hydrogen fuel, a fuel blend having 50-100% hydrogen, a fuel blend having 0-60% hydrogen, natural gas fuel or fuel blend, hydrocarbon fuel or fuel blend, a fuel-air mixture having 0-50% fuel or fuel blend and 0-50% air, or combinations thereof. In some non-limiting examples: hydrogen fuel may be supplied along a first fuel flow path 91; a fuel blend having 50-100% hydrogen may be supplied along the first fuel flow path 91; natural gas fuel may be supplied along a second fuel flow path 92; or a fuel blend having 0-60% hydrogen may be supplied along the second fuel flow path 92. It is also contemplated that fuel injection along the central fuel passage 85 may form a pilot during natural gas operation, or in some examples for a low blend of hydrogen fuel (e.g., 0-50% hydrogen). In some examples, the turbine engine 10 ( Figure 1 Natural gas fuel can be initiated by combustion via a fuel-air mixer 35 and then converted to other fuels, such as a low percentage (e.g., 0-50%) hydrogen fuel blend at low power levels and a high percentage (e.g., 50-100%) hydrogen fuel blend at high power levels. In some examples, turbine engine 10 ( Figure 1 It can use natural gas fuel to initiate combustion via fuel-air mixer 35, and convert it into 100% hydrogen fuel at maximum power. In some examples, turbine engine 10 ( Figure 1 It can operate with a high percentage of hydrogen fuel at low power levels and with natural gas fuel at high power levels.

[0067] Go to Figure 7 Along line VII-VII ( Figure 5 An alternative cross-sectional view of the fuel-air mixer 35 is shown. A body 70 with a first portion 70A and a second portion 70B is shown. As described above, a set of outlets 78 can form a fuel outlet 58.

[0068] In this view, the inner wall 72 is shown within a set of mixing channels 81 and has a set of inner orifices 72A. An external view of the third wall 73 and the third set of orifices 73A is also shown. In some examples, the third wall 73 may be circumferentially offset relative to the central axis C from either the outer wall 71 or the inner wall 72, or both.

[0069] Inlet flow path 93 is shown as passing through a set of inlets 71A. Central air flow path 94 is shown as extending from central air passage 86, passing through a set of inner orifices 72A, and entering a set of mixing passages 81. First fuel flow path 91 is shown as extending from a second set of passages 82, passing through a set of outer orifices 73A, and entering a set of mixing passages 81. Second fuel flow path 92 is shown as extending from central fuel passage 85, passing through a set of central orifices 76A, and entering a set of outlet mixing passages 88.

[0070] It is conceivable that fuel, fuel blends, or fuel-air mixtures can be injected along multiple flow paths at different or staggered axial positions relative to the central axis C. In some examples, a second fuel flow path 92 can inject fuel downstream of fuel injected from a set of internal orifices 72A. This staggered arrangement can provide fuel concentration differences between a set of outlets 78, which can reduce undesirable combustion dynamics.

[0071] Figure 8 The fuel-air mixer 35 is shown along Figure 7 The front cross-sectional view of line VIII-VIII. The illustrated view is taken from a set of exits 78 ( Figure 7 Upstream of ). In this view, portions of the central fuel passage 85, central air passage 86, and a set of outlet mixing passages 88 are shown in the body 70 relative to the central axis C. Figure 7 At one axial position.

[0072] A set of outlet mixing channels 88 can be located relative to the central axis C ( Figure 7 The set of outlet mixing channels 88 has a constant cross-sectional area in the direction toward the set of outlets 78, with either an increasing or decreasing cross-sectional area. It is also envisioned that the geometry of the set of outlet mixing channels 88 can be circular, elliptical, or a combination thereof. In some examples, the set of outlet mixing channels 88 may include a circular cross-sectional profile at a first axial position and with respect to the central axis C(…).Figure 7 At the second axial position, it transitions to an elliptical cross-sectional profile. In some examples, a set of outlet mixing channels 88 may include a first elliptical profile at a first axial position and a second elliptical profile at a second axial position, wherein the first and second elliptical profiles are oriented in different directions. In this way, a set of outlet mixing channels 88 can be configured to guide the outlet flow of fuel, air, or a mixture thereof in multiple directions, including parallel to the central axis C(…). Figure 7 ) guides the outlet flow of fuel, air, or their mixture around the central axis C ( Figure 7 ) Circumferentially guides the outlet flow of fuel, air, or their mixture relative to the central axis C( Figure 7 The outlet flow of fuel, air, or a mixture thereof, or a combination thereof, is directed radially. Any one or both of a set of outlet mixing channels 88 or a set of outlets 78 may be configured to provide a swirling fluid flow, a jet, a radial fluid flow, etc., or a combination thereof, for combustion chamber 50. Figure 3 Combustion within.

[0073] In this way, the fuel-air mixer 35 can have an internal mixer air passage that divides the air into multiple discrete streams, forming an inlet to the combustion chamber 50. Figure 3 Multiple discrete outlets (e.g., a set of outlets 78). Fuel can be injected into multiple discrete streams from multiple discrete orifices (e.g., a set of inner orifices 72A) or from a central fuel passage 85 (e.g., a set of central orifices 76A) or a combination thereof.

[0074] Now for reference Figure 9 This shows that it can be used in burner 30 ( Figure 3 Another fuel-air mixer 135 used in ) is similar to fuel-air mixer 35; therefore, similar parts will be identified by similar numbers increasing by 100, and it should be understood that the description of similar parts of fuel-air mixer 35 applies to fuel-air mixer 135 unless otherwise stated.

[0075] The fuel-air mixer 135 may include a body 170 having a central axis C, a set of inlets 171A, and a set of outlets 178. The body 170 may also include a set of mixing channels 181, a second set of channels 182, a central fuel channel 185, a central air channel 186, and a set of outlet mixing channels 188. A fourth set of orifices 174A fluidly connects the set of mixing channels 181 to the set of outlets 178. A set of central orifices 176A fluidly connects the central fuel channel 185 and the set of outlet mixing channels 188.

[0076] One difference is that the body 170 can define a first length L1, a second length L2, a third length L3, and a fourth length L4. The first length L1 can be defined between a set of outlets 178 and a set of inlets 171A. The second length L2 can be defined between a set of outlets 178 and a set of fourth orifices 174A. The third length L3 can be defined between a set of outlets 178 and a set of central orifices 176A. The fourth length L4 can be defined along a portion of a set of outlet mixing channels 188, which has at least one flow transition, such as a change in cross-sectional area, shape, etc.

[0077] It is conceivable that any of the first length L1, second length L2, third length L3, or fourth length L4 can be formed relative to each other in a predetermined ratio or relative value. In some examples, the second length L2 can be a predetermined percentage of the first length L1, or the third length L3 can be a predetermined percentage of the first length L1, or the fourth length L4 can be a predetermined percentage of the second length L2. In some examples, the second length L2 can be between 5% and 95% of the first length L1, or between 10% and 90% of the first length L1, or between 20% and 80% of the first length L1, and so on. In some examples, the third length L3 can be between 2% and 100% of the first length L1. In some examples, the fourth length L4 can be between 5% and 100% of the second length L2.

[0078] The body 170 may also define an inner surface 189 and an outer surface 190 along a set of outlet mixing channels 188. One or both of the inner surface 189 or the outer surface 190 may be parallel to the central axis C, or form a positive angle (in some examples, away from the central axis C), or form a negative angle (in some examples, towards the central axis C) relative to the central axis C. It is also envisioned that the cross-sectional area of ​​the outlet channels in the set of outlet mixing channels 188 may be constant, increasing, or decreasing in the direction toward the set of outlets 178. In this way, flow can be directed to the set of outlets 178 at a predetermined speed and angle.

[0079] A set of outlets 178 may also have an outlet direction 200 forming an outlet angle 201, as shown. The outlet angle 201 may be formed relative to the central axis C or relative to a direction along the central fuel passage 185. In the example shown, the central fuel passage 185 extends parallel to the central axis C, such that the outlet angle 201 is formed relative to both the central axis C and the central fuel passage 185, although this is not mandatory. In the non-limiting example shown, the outlet direction 200 forms a positive outlet angle 201, such that fuel and air diverge radially away from the central axis C as they leave the body 170. In this way, the overall flow direction can be radially outward through the set of outlet mixing passages 188. In other examples, multiple outlets in a set of outlets 178 may have different outlet directions 200, such as alternating outlet directions, multiple sets of identical outlet directions, randomly arranged outlet directions, etc.

[0080] Figure 10 and 11 The front view and the view along the sides of the fuel-air mixer 135 are shown respectively. Figure 9 The front cross-sectional view of line XI-XI. Figure 10 In the diagram, a set of outlets 178 is shown together with a set of outlet mixing channels 188. The set of outlet mixing channels 188 is positioned relative to the central axis C ( Figure 9 The cross-sectional area of ​​the set of outlets 178 can be constant, increasing, or decreasing in the direction toward which they are directed. It is also envisioned that the geometry of the set of outlet mixing channels 188 can be circular, elliptical, or a combination thereof. In this way, the set of outlet mixing channels 188 can be configured to guide the outlet flow of fuel, air, or a mixture thereof in multiple directions. In some examples, the set of outlet mixing channels 188 can be parallel to the central axis C(…). Figure 9 ) Oriented or extended around the central axis C ( Figure 9 ) Circumferentially oriented or extended, relative to the central axis C ( Figure 9 Radially oriented or extended, or a combination thereof. Any one or both of a set of outlet mixing channels 188 or a set of outlets 178 may be configured to provide a swirling fluid flow, a jet, a radial fluid flow, etc., or a combination thereof, for combustion chamber 50. Figure 3 Combustion within.

[0081] Now for reference Figure 12 This shows that it can be used in burner 30 ( Figure 3 Another fuel-air mixer 235 used in ) is similar to fuel-air mixers 35 and 135; therefore, similar parts will be identified by similar numbers further increased by 100. It should be understood that the description of similar parts of fuel-air mixers 35 and 135 applies to fuel-air mixer 235 unless otherwise stated.

[0082] The fuel-air mixer 235 may include a body 270 having a central axis C, a set of inlets 271A, and a set of outlets 278. The body 270 may also include a set of mixing channels 281, a second set of channels 282, a central fuel channel 285, a central air channel 286, and a set of outlet mixing channels 288. A fourth set of orifices 274A fluidly connects the set of mixing channels 281 to the set of outlets 278. A set of central orifices 276A fluidly connects the central fuel channel 285 and the set of outlet mixing channels 288.

[0083] Body 270 may define a first length L1, a second length L2, a third length L3, and a fourth length L4. The first length L1 may be defined between a set of outlets 278 and a set of inlets 271A. The second length L2 may be defined between a set of outlets 278 and a fourth set of orifices 274A. The third length L3 may be defined between a set of outlets 278 and a set of central orifices 276A. The fourth length L4 may be defined along a portion of a set of outlet mixing channels 288, which has at least one flow transition, such as a changing cross-sectional area, shape, etc.

[0084] It is conceivable that any of the first length L1, second length L2, third length L3, or fourth length L4 can be formed relative to each other in a predetermined ratio or relative value. In some examples, the second length L2 can be a predetermined percentage of the first length L1, or the third length L3 can be a predetermined percentage of the first length L1, or the fourth length L4 can be a predetermined percentage of the second length L2. In some examples, the second length L2 can be between 5% and 95% of the first length L1, or between 10% and 90% of the first length L1, or between 20% and 80% of the first length L1, and so on. In some examples, the third length L3 can be between 2% and 100% of the first length L1. In some examples, the fourth length L4 can be between 5% and 100% of the second length L2.

[0085] The body 270 may also define an inner surface 289 and an outer surface 290 along a set of outlet mixing channels 288. One or both of the inner surface 289 or the outer surface 290 may be parallel to the central axis C, forming a positive angle or a negative angle relative to the central axis C. In the example shown, the outer surface 290 is parallel to the central axis C and the inner surface 289 forms a negative angle (e.g., convergence) relative to the central axis C.

[0086] A set of outlets 278 may also have an outlet direction 300 forming an outlet angle 301, as shown in the figure. The outlet angle 301 may be formed relative to the central axis C or relative to a direction along the central fuel passage 285. In the non-limiting example shown, the outlet direction 300 forms a negative outlet angle 301, such that fuel and air converge toward the central axis C as they leave the body 270.

[0087] Figure 13 and 14 The front view and the view along the sides of the fuel-air mixer 235 are shown respectively. Figure 12 The front cross-sectional view of line XIV-XIV. In this view, a set of outlets 278 are shown together with a set of outlet mixing channels 288. The set of outlet mixing channels 288 is positioned relative to the central axis C ( Figure 12 The cross-sectional area of ​​the set of outlets 278 can be constant, increasing, or decreasing. It is also envisioned that the geometry of the set of outlet mixing channels 288 can be circular, elliptical, or a combination thereof. In this way, the set of outlet mixing channels 288 can be configured to guide the outlet flow of fuel, air, or a mixture thereof in multiple directions. The set of outlet mixing channels 188 can be parallel to the central axis C(…). Figure 12 ) Oriented or extended around the central axis C ( Figure 12 ) Circumferentially oriented or extended, relative to the central axis C ( Figure 12 Radially oriented or extended, or a combination thereof. Either or both of a set of outlet mixing channels 288 or a set of outlets 278 may be configured to provide swirling fluid flow, jet, radial fluid flow, etc., or combinations thereof, for combustion chamber 50. Figure 3 Combustion within.

[0088] Now for reference Figure 15 This shows that it can be used in burner 30 ( Figure 3 Another fuel-air mixer 335 used in ) is similar to fuel-air mixers 35, 135, and 235; therefore, similar parts will be identified by similar numbers further increased by 100. It should be understood that the description of similar parts of fuel-air mixers 35, 135, and 235 applies to fuel-air mixer 335 unless otherwise stated.

[0089] The fuel-air mixer 335 may include a body 370 having a central axis C, a set of inlets 371A, and a set of outlets 378. The body 370 may also include a set of mixing channels 381, a second set of channels 382, ​​a central fuel channel 385, a central air channel 386, and a set of outlet mixing channels 388. A fourth set of orifices 374A fluidly connects the set of mixing channels 381 to the set of outlets 378. A set of central orifices 376A fluidly connects the central fuel channel 385 and the set of outlet mixing channels 388.

[0090] The body 370 may define a first length L1, a second length L2, a third length L3, and a fourth length L4. The first length L1 may be defined between a set of outlets 378 and a set of inlets 371A. The second length L2 may be defined between a set of outlets 378 and a fourth set of orifices 374A. The third length L3 may be defined between a set of outlets 378 and a set of central orifices 376A. The fourth length L4 may be defined along a portion of a set of outlet mixing channels 388, which has at least one flow transition, such as a change in cross-sectional area, shape, etc.

[0091] It is conceivable that any of the first length L1, second length L2, third length L3, or fourth length L4 can be formed relative to each other in a predetermined ratio or relative value. In some examples, the second length L2 can be a predetermined percentage of the first length L1, or the third length L3 can be a predetermined percentage of the first length L1, or the fourth length L4 can be a predetermined percentage of the second length L2. In some examples, the second length L2 can be between 5% and 95% of the first length L1, or between 10% and 90% of the first length L1, or between 20% and 80% of the first length L1, and so on. In some examples, the third length L3 can be between 2% and 100% of the first length L1. In some examples, the fourth length L4 can be between 5% and 100% of the second length L2.

[0092] The body 370 may also define an inner surface 389 and an outer surface 390 along a set of outlet mixing channels 388. One or both of the inner surface 389 or the outer surface 390 may be parallel to the central axis C, forming a positive angle (e.g., diverging) or a negative angle (e.g., converging) relative to the central axis C. In the non-limiting example shown, the outer surface 390 forms a positive angle (e.g., diverging) relative to the central axis C, and the inner surface 389 is parallel to the central axis C.

[0093] A set of outlets 378 may also have an outlet direction 400 forming an outlet angle 401, as shown. The outlet angle 401 may be formed relative to the central axis C or relative to a direction along the central fuel passage 385. In the non-limiting example shown, the outlet direction 400 forms a very small positive outlet angle 401, such that the fuel and air exit the body 370 generally parallel to or slightly diverge from the central axis C. It is anticipated that the cross-section along the set of outlet mixing passages 188 may be oriented at least partially along the central axis C and the overall flow direction may be radially outward from the central axis C.

[0094] Figure 16 and 17 The front view and the view along the sides of the fuel-air mixer 335 are shown respectively. Figure 15 The front cross-sectional view of line XVII-XVII. Figure 16 In the diagram, a set of outlets 378 is shown together with a set of outlet mixing channels 388. The set of outlet mixing channels 388 is positioned relative to the central axis C ( Figure 15 The cross-sectional area of ​​the set of outlets 378 can be constant, increasing, or decreasing in the direction toward the set of outlets 378. It is also anticipated that the geometry of the set of outlet mixing channels 388 can be circular, elliptical, or a combination thereof. In this way, the set of outlet mixing channels 388 can be configured to guide the outlet flow of fuel, air, or a mixture thereof in multiple directions, including parallel to the central axis C(…). Figure 15 ) guides the outlet flow of fuel, air, or their mixture around the central axis C ( Figure 15 ) Circumferentially guides the outlet flow of fuel, air, or their mixture relative to the central axis C( Figure 15 The outlet flow of fuel, air, or a mixture thereof, or a combination thereof, is radially directed. Any one or both of a set of outlet mixing channels 388 or a set of outlets 378 may be configured to provide a swirling fluid flow, a jet, a radial fluid flow, etc., or a combination thereof, for combustion chamber 50. Figure 3 Combustion within.

[0095] Overall reference Figures 1-17This disclosure provides a method for supplying a fuel-air mixture, including an enriched fuel-air mixture, to a turbine engine combustion chamber. The method may include supplying air through air passages (e.g., central air passages 86, 186, 286, 386) extending along an axis (e.g., a central axis (C)). The method may further include separating the air from the central air passages 86, 186, 286, 386 among a set of mixing passages, such as a set of mixing passages 81, 181, 281, 381 located radially outside the air passages. The method may further include supplying fuel to the set of mixing passages 81, 181, 281, 381 to form a fuel-air mixture within the set of mixing passages 81, 181, 281, 381. The method may further include guiding the fuel-air mixture to a set of outlet mixing passages 88, 188, 288, 388, at least one of which extends axially or radially relative to the axis (C). The method may also include supplying fuel from a second set of channels, such as second set of channels 82, 182, 282, 382, ​​to a set of mixing channels 81, 181, 281, 381.

[0096] The method may further include supplying additional fuel to at least one set of outlet mixing channels 88, 188, 288, 388, and supplying it to the fuel-air mixture therein to form a enriched fuel-air mixture. As described above, the enriched fuel-air mixture may be supplied to the fuel outlet and enter the combustion chamber.

[0097] The above aspects offer several benefits. The internal mixer air passages, divided into multiple discrete flows, can provide improved fuel distribution within the fuel-air mixer, which can increase strain rate and mixing efficiency. This arrangement can provide temperature reduction and the elimination of unwanted combustion byproducts (including NO). x The present disclosure also provides a shorter and more compact flame compared to conventional fuel injectors. In one non-limiting example, the flame length provided by the present disclosure is less than half the flame size in a conventional burner. The multiple discrete streams and staggered axial injections described herein also provide improved flow diffusion within the burner downstream of the fuel outlet, a shift in flame position away from the burner bushing, and a more uniform fuel-air mixture at the fuel outlet. The high-speed jets generated from the discrete outlets also generate high turbulence within the combustion chamber, resulting in better mixing and a more uniform temperature distribution within the burner, thereby reducing NO. x emission.

[0098] Furthermore, using multiple axial lengths for a set of air inlets or a set of internal channels can provide different mixing lengths within the fuel-air mixer body. Such an arrangement allows for selection or customization of the fuel-air distribution between the fuel-air mixer outlets, driving differences in heat release rates and reducing undesirable combustion dynamics.

[0099] Although a turbine engine has been described, it should be understood that aspects of this disclosure can have general applicability to any combustor. In a non-limiting example, aspects of this disclosure described herein may also be applied to engines, turbojet engines, or turboshaft engines having propeller sections, fan and booster sections.

[0100] Within the scope not described herein, various features and structures of different embodiments may be combined or substituted for each other as needed. The fact that a feature is not shown in all embodiments does not mean that it cannot be shown so, but rather that it is done for the sake of brevity. Therefore, various features of different embodiments may be mixed and matched as needed to form new embodiments, regardless of whether the new embodiments are explicitly described. All combinations or permutations of the features described herein are covered by this disclosure.

[0101] Further aspects of this disclosure are provided in the following terms:

[0102] A turbine engine includes: a compressor section, a combustion section, and a turbine section arranged in an axial flow configuration, wherein the combustion section has a combustor, the combustor including: a combustor bushing at least partially defining a combustion chamber; a compressed air passage fluidly coupled to the compressor section and the combustion chamber; at least one fuel supply fluidly coupled to the combustion chamber; and a fuel-air mixer including: a body extending along a central axis and having an outer wall; and an inner wall located within the body and defining a fluid connection to the compressed air. A central air passage, wherein an inner wall is spaced apart from an outer wall to at least partially define a set of mixing channels between the inner and outer walls, wherein the set of mixing channels is spaced radially outward of the central air passage relative to a central axis; a central wall located radially inward of the inner wall and forming a central fuel passage fluidly connected to the at least one fuel supply; a set of internal orifices in the inner wall fluidly connecting the central air passage to the set of mixing channels; and a central airflow path extending from the central air passage to the set of mixing channels.

[0103] In any of the preceding clauses, the turbine engine wherein the central air passage at least partially surrounds the central fuel passage.

[0104] The turbine engine according to any of the foregoing clauses further includes: a set of outlet mixing passages fluidly connected to the combustion chamber; and a set of central orifices in the central wall fluidly connected to the central fuel passages.

[0105] The turbine engine according to any of the foregoing clauses further includes a set of inlets in the outer wall of the body and fluidly connected to the set of mixing channels.

[0106] The turbine engine according to any of the foregoing clauses further includes a third wall, which is located within the body and forms a second set of channels.

[0107] The turbine engine according to any of the foregoing clauses further includes a third set of orifices in the third wall, the third set of orifices fluidly connecting the second set of channels to the set of mixing channels.

[0108] The turbine engine according to any of the foregoing clauses, wherein the set of central orifices is located behind the set of inlets relative to the central axis.

[0109] The turbine engine according to any of the foregoing clauses, wherein the set of inlets is located behind the third set of orifices.

[0110] The turbine engine according to any of the foregoing clauses further includes: a first fuel flow path extending sequentially from the second set of channels to the set of mixing channels and to the set of outlet mixing channels; and a second fuel flow path extending from the central fuel channel to the set of outlet mixing channels.

[0111] According to any of the foregoing clauses, the set of inlets includes inlets axially spaced apart relative to the central axis.

[0112] According to any of the foregoing clauses, the set of outlet mixing channels extends axially and radially relative to the central axis.

[0113] According to any of the preceding clauses, the set of outlet mixing channels extends axially and circumferentially relative to the central axis of the turbine engine.

[0114] The turbine engine according to any of the foregoing clauses further includes a set of outlets in the body, the set of outlets being fluidly coupled to the set of outlet mixing channels.

[0115] The turbine engine according to any of the foregoing clauses further includes a first length defined between the set of inlets and the set of outlets, a second length defined between the set of outlets and the fourth set of orifices, and a third length defined between the set of outlets and the set of central orifices.

[0116] According to any of the preceding clauses, the turbine engine further defines a fourth length defined along a portion of the set of outlet mixing channels, said portion having a flow transition including at least one of a varying cross-sectional area or a varying channel shape.

[0117] The turbine engine according to any of the foregoing clauses, wherein the second length is between 20% and 80% of the first length.

[0118] According to any of the foregoing clauses, the second length is between 10% and 90% of the first length.

[0119] According to any of the foregoing clauses, the second length is between 5% and 95% of the first length of the turbine engine.

[0120] According to any of the preceding clauses, the third length is between 2% and 100% of the first length of the turbine engine.

[0121] According to any of the preceding clauses, the fourth length is between 5% and 100% of the second length of the turbine engine.

[0122] The turbine engine according to any of the foregoing clauses further includes the inner and outer surfaces of the outlet passages along the set of outlet mixing passages.

[0123] According to any of the preceding clauses, in a turbine engine, at least one of the inner surface or the outer surface forms a positive angle relative to the second axis.

[0124] According to any of the preceding clauses, in a turbine engine, at least one of the inner surface or the outer surface forms a negative angle relative to the second axis.

[0125] A combustor for a turbine engine includes: a combustor bushing that at least partially defines a combustion chamber; a compressed air passage that fluidly connects a compressed air source to the combustion chamber; at least one fuel supply that is fluidly connected to the combustion chamber; and a fuel-air mixer comprising: a body extending along a central axis and having an outer wall; an inner wall located within the body and defining a central air passage fluidly connected to the compressed air passage, wherein the inner wall is spaced apart from the outer wall to at least partially define a set of mixing channels between the inner wall and the outer wall, wherein the set of mixing channels is spaced radially outward of the central air passage relative to the central axis; a central wall located radially inward of the inner wall and forming a central fuel passage fluidly connected to the at least one fuel supply; a set of internal orifices in the inner wall that fluidly connect the central air passage to the set of mixing channels; and a central airflow path extending from the central air passage to the set of mixing channels.

[0126] According to any of the foregoing clauses, the central air passage at least partially surrounds the central fuel passage.

[0127] The burner according to any of the foregoing clauses further includes: a set of outlet mixing channels fluidly connected to the combustion chamber; and a set of central orifices in the central wall fluidly connected to the central fuel channel.

[0128] The burner according to any of the foregoing clauses further includes a set of inlets in the outer wall of the body and fluidly connected to the set of mixing channels.

[0129] The burner according to any of the foregoing clauses further includes a third wall within the body and forms a second set of channels.

[0130] The burner according to any of the foregoing clauses further includes a third set of orifices in the third wall, the third set of orifices fluidly connecting the second set of channels to the set of mixing channels.

[0131] The burner according to any of the foregoing clauses further includes a set of outlets in the body, the set of outlets being fluidly connected to the set of outlet mixing channels.

[0132] The burner according to any of the foregoing clauses further includes a first length defined between the set of inlets and the set of outlets, a second length defined between the set of outlets and the fourth set of orifices, and a third length defined between the set of outlets and the set of central orifices.

[0133] According to any of the preceding clauses, the burner further defines a fourth length defined along a portion of the set of outlet mixing channels, said portion having a flow transition including at least one of a varying cross-sectional area or a varying channel shape.

[0134] According to any of the preceding clauses, the second length is between 20% and 80% of the first length.

[0135] According to any of the preceding clauses, the second length is between 10% and 90% of the first length.

[0136] According to any of the preceding clauses, the second length is between 5% and 95% of the first length.

[0137] According to any of the preceding clauses, the third length is between 2% and 100% of the first length.

[0138] According to any of the preceding clauses, the fourth length is between 5% and 100% of the second length.

[0139] The burner according to any of the foregoing clauses further includes the inner and outer surfaces of the outlet channels along the set of outlet mixing channels.

[0140] According to any of the preceding clauses, in a burner, at least one of the inner surface or the outer surface forms a positive angle with respect to the second axis.

[0141] According to any of the preceding clauses, in a burner, at least one of the inner surface or the outer surface forms a negative angle relative to the second axis.

[0142] A method for supplying a fuel-air mixture to a turbine engine combustion chamber, the method comprising: supplying air through an air passage extending along an axis; separating the air from the air passage in a set of mixing passages located radially outside the air passage; supplying fuel to the set of mixing passages to form a fuel-air mixture within the set of mixing passages; and guiding the fuel-air mixture to a set of outlet mixing passages, at least one of the set of outlet mixing passages extending axially or radially relative to the axis.

[0143] According to any of the foregoing provisions, supplying fuel includes supplying fuel from the second set of channels to the set of mixing channels.

[0144] The method according to any of the foregoing clauses further includes supplying additional fuel to at least one set of outlet mixing channels and to the fuel-air mixture to form an enriched fuel-air mixture.

Claims

1. A turbine engine, characterized in that, include: A compressor section, a combustion section, and a turbine section are arranged in an axial flow configuration, wherein the combustion section includes a burner comprising: A burner bushing that at least partially defines a combustion chamber; A compressed air passage, which is fluidly connected to the compressor section and the combustion chamber; At least one fuel supply device, said at least one fuel supply device being fluidly coupled to said combustion chamber; and A fuel-air mixer, the fuel-air mixer comprising: A body, which extends along a central axis and has an outer wall; An inner wall located within the body and defining a central air passage fluidly connected to the compressed air passage, wherein the inner wall is spaced apart from the outer wall to at least partially define a set of mixing channels between the inner wall and the outer wall, wherein the set of mixing channels is spaced radially outward of the central air passage relative to the central axis; A central wall, located radially inside the inner wall, and forming a central fuel passage fluidly connected to the at least one fuel supply, wherein the central air passage at least partially surrounds the central fuel passage; A set of internal openings in the inner wall fluidly connects the central air passage to the set of mixing channels; and A central airflow path that extends from the central air channel to the set of mixing channels; A set of outlet mixing channels, the set of outlet mixing channels being fluidly connected to the combustion chamber; and A set of central orifices in the central wall fluidly connects the central fuel passage to the set of outlet mixing passages; A set of inlets, which are located in the outer wall of the body and fluidly connected to the set of mixing channels; A third wall, which is located within the body and forms a second set of channels; A first fuel flow path extends sequentially from the second set of channels to the set of mixing channels and then to the set of outlet mixing channels; and A second fuel flow path extends directly from the central fuel channel to the set of outlet mixing channels.

2. The turbine engine according to claim 1, characterized in that, The system further includes a third set of orifices in the third wall, which fluidly connect the second set of channels to the set of mixing channels.

3. The turbine engine according to claim 2, characterized in that, in, The set of central openings is located behind the set of inlets relative to the central axis.

4. The turbine engine according to claim 3, characterized in that, in, The first set of entrances is located behind the third set of orifices.

5. The turbine engine according to any one of claims 1-4, characterized in that, in, The set of inlets is axially spaced relative to the central axis.

6. The turbine engine according to any one of claims 1-4, characterized in that, in, The set of outlet mixing channels extends axially and radially relative to the central axis.

7. A combustor for a turbine engine, characterized in that, include: A burner bushing that at least partially defines a combustion chamber; A compressed air passage that fluidly connects a compressed air source to the combustion chamber; At least one fuel supply device, said at least one fuel supply device being fluidly coupled to said combustion chamber; and A fuel-air mixer, the fuel-air mixer comprising: A body, which extends along a central axis and has an outer wall; An inner wall located within the body and defining a central air passage fluidly connected to the compressed air passage, wherein the inner wall is spaced apart from the outer wall to at least partially define a set of mixing channels between the inner wall and the outer wall, wherein the set of mixing channels is spaced radially outward of the central air passage relative to the central axis; A central wall, located radially inside the inner wall, and forming a central fuel passage fluidly connected to the at least one fuel supply, wherein the central air passage at least partially surrounds the central fuel passage; A set of internal openings in the inner wall fluidly connects the central air passage to the set of mixing channels; and A central airflow path that extends from the central air channel to the set of mixing channels; A set of outlet mixing channels, the set of outlet mixing channels being fluidly connected to the combustion chamber; and A set of central orifices in the central wall fluidly connects the central fuel passage to the set of outlet mixing passages; A set of inlets, which are located in the outer wall of the body and fluidly connected to the set of mixing channels; A third wall, which is located within the body and forms a second set of channels; A first fuel flow path extends sequentially from the second set of channels to the set of mixing channels and then to the set of outlet mixing channels; and A second fuel flow path extends directly from the central fuel channel to the set of outlet mixing channels.

8. The burner according to claim 7, characterized in that, It further includes a third set of orifices in the third wall, the third set of orifices fluidly connecting the second set of channels to the set of mixing channels.

9. A method for supplying a fuel-air mixture to a turbine engine combustion chamber, characterized in that, The method includes: Air is supplied through air channels extending along the axis; The air from the air passage is separated in a set of mixing channels located radially outside the air passage; Fuel is supplied to the set of mixing channels to form a fuel-air mixture within the set of mixing channels; and The fuel-air mixture is guided to a set of outlet mixing channels, the set of outlet mixing channels extending axially or radially relative to the axis at least once, wherein supplying fuel includes supplying fuel from a second set of channels to the set of mixing channels, wherein a first fuel flow path extends sequentially from the second set of channels to the set of mixing channels and to the set of outlet mixing channels, and a second fuel flow path extends directly from the central fuel channel to the set of outlet mixing channels.

10. The method according to claim 9, characterized in that, Further, it includes supplying additional fuel to at least one set of outlet mixing channels and to the fuel-air mixture to form an enriched fuel-air mixture.

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