Burner fuel nozzle assemblies

Abstract

A turbine engine may include a compressor section, a combustion section, and a turbine section in a serial flow arrangement. A combustor in the combustion section may include a combustion chamber, a fuel supply fluidically coupled to the combustion chamber, and a fuel nozzle assembly. The fuel nozzle assembly may include an air flow passage and a fuel flow passage.

Description

[0001] CROSS-REFERENCE TO RELATED APPLICATIONS

[0002] This application claims the benefit of U.S. Provisional Patent Application No. 63 / 299,619, filed January 14, 2022, and U.S. Patent Application No. 17 / 725,895, filed April 21, 2022, both of which are incorporated herein by reference in their entireties. Technical Field

[0003] The present subject matter relates generally to combustors having fuel nozzle assemblies for turbine engines and, more particularly, to fuel nozzle assemblies having multiple injection arrangements. Background Art

[0004] The turbine engine is driven by a flow of combustion gases through the engine to rotate a plurality of turbine blades. A combustor may be disposed within the turbine engine and fluidly coupled to the turbine into which the combustion gases flow.

[0005] In a typical turbine engine, air and fuel are supplied to a combustion chamber, mixed, and then ignited to produce hot gases. The hot gases are then fed to a turbine, which spins the turbine to generate power. BRIEF DESCRIPTION OF THE DRAWINGS

[0006] In the attached figure:

[0007] Figure 1 is a schematic cross-sectional illustration of a turbine engine having a compression section, a combustion section, and a turbine section according to various aspects described herein.

[0008] Figure 2 Yes, you can Figure 1 Cross-sectional view of a generic combustor used in a turbine engine.

[0009] Figure 3 According to various aspects described herein, Figure 1 A cross-sectional view of another combustor having a fuel nozzle assembly for use in a turbine engine.

[0010] Figure 4 yes Figure 3 Top view of a portion of a burner, showing a set of dilution holes.

[0011] Figure 5 It is along the VV line Figure 3 A cross-sectional view of a fuel nozzle assembly. DETAILED DESCRIPTION

[0012] The disclosed aspects described herein are directed to a combustor having a fuel nozzle assembly. For purposes of illustration, the present disclosure will be described with respect to a turbine engine. However, it will be understood that the disclosed aspects described herein are not limited thereto, and the combustor described herein can be implemented in engines including, but not limited to, turbojets, turboprops, turboshafts, and turbofans. The disclosed aspects discussed herein can have general applicability in non-aircraft engines having a combustor, such as in other mobile applications and non-mobile industrial, commercial, and residential applications.

[0013] The word "exemplary" is used herein to mean "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other implementations. Furthermore, all embodiments described herein are to be considered exemplary unless expressly stated otherwise.

[0014] As used herein, the terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another and are not intended to indicate the position or importance of each component.

[0015] The terms "fore" 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, the front position refers to the position closer to the engine inlet, while the aft position refers to the position closer to the engine nozzle or exhaust.

[0016] As used herein, the term "upstream" refers to a direction opposite to the direction of fluid flow, while the term "downstream" refers to a direction in the same direction as the direction of fluid flow. The terms "forward" or "front" mean in front of something, and "rearward" or "rear" mean behind something. For example, when used in relation to fluid flow, forward / front can refer to upstream, and rearward / rear can refer to downstream.

[0017] The term "fluid" may be a gas or a liquid. The term "fluid communication" may be used herein to mean that a fluid is able to establish a connection between designated areas.

[0018] Additionally, as used herein, the term "radial" or "radially" refers to directions away from a common center. For example, in the overall context of a turbine engine, radial refers to directions along a ray extending between the central longitudinal axis of the engine and the periphery of the engine.

[0019] All directional references (e.g., radial, axial, proximal, distal, up, down, upward, downward, left, right, lateral, front, back, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, backward, etc.) are used for identification purposes only to assist the reader in understanding the present disclosure and do not impose limitations, particularly with respect to the position, orientation, or use of the disclosed aspects described herein. Connection references (e.g., attach, couple, connect, and join) are to be interpreted broadly and may include intermediate structural elements between a collection of elements and relative movement between elements, unless otherwise indicated. Thus, a connection reference does not necessarily mean that two elements are directly connected and fixed relative to each other. The exemplary figures are for illustrative purposes only, and the dimensions, positions, order, and relative sizes reflected in the accompanying figures may vary.

[0020] The singular forms "a," "an," and "the" include plural references unless the context clearly dictates otherwise. Also, as used herein, the term "set" or "a group of" elements may refer to any number of elements, including only one.

[0021] As used herein throughout the specification and claims, approximating language is applied to modify any quantitative expression that can be allowed to vary without causing a change in its associated basic function. Therefore, values ​​modified by one or more terms such as "approximately," "approximately," "substantially," and "substantially" are not limited to the precise values ​​specified. In at least some cases, approximate language can correspond to the precision of an instrument used to measure a value, or the precision of a method or machine used to construct or manufacture a component and / or system. In at least some cases, approximate language can correspond to the precision of an instrument used to measure a value, or the precision of a method or machine used to construct or manufacture a component and / or system. For example, approximate language can refer to being within 1%, 2%, 4%, 5%, 10%, 15%, or 20% of an endpoint of a single value, a range of values, and / or a range of values. Here, as well as throughout the specification and claims, range limitations are combined and interchanged, and such ranges are identified and include all subranges contained therein unless the context or language indicates otherwise. For example, all ranges disclosed herein include the endpoints, and the endpoints can be combined independently of each other.

[0022] Figure 1 is a schematic diagram of a turbine engine 10. As a non-limiting example, the turbine engine 10 may be used within an aircraft. The turbine engine 10 may include at least a compressor section 12, a combustion section 14, and a turbine section 16. A drive shaft 18 rotationally couples the compressor section 12 and the turbine section 16 so that rotation of one affects rotation of the other and defines an axis of rotation 20 of the turbine engine 10.

[0023] The compressor section 12 may include a low-pressure (LP) compressor 22 and a high-pressure (HP) compressor 24 fluidly coupled in series with each other. The turbine section 16 may include an HP turbine 26 and an LP turbine 28 fluidly coupled in series with each other. The drive shaft 18 may operably couple the LP compressor 22, the HP compressor 24, the HP turbine 26, and the LP turbine 28 together. Alternatively, the drive shaft 18 may include an LP drive shaft (not shown) and an HP drive shaft (not shown). The LP drive shaft may couple the LP compressor 22 to the LP turbine 28, and the HP drive shaft may couple the HP compressor 24 to the HP turbine 26. The LP spool may be defined as the combination of the LP compressor 22, the LP turbine 28, and the LP drive shaft, such that rotation of the LP turbine 28 may apply driving force to the LP drive shaft, which in turn may rotate the LP compressor 22. The HP spool may be defined as the combination of the HP compressor 24, the HP turbine 26, and the HP drive shaft, such that rotation of the HP turbine 26 may apply driving force to the HP drive shaft, which in turn may rotate the HP compressor 24.

[0024] The compressor section 12 may include a plurality of axially spaced stages. Each stage includes a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary vanes. The compressor blades for a stage of the compressor section 12 may be mounted to a disk, which is mounted to the drive shaft 18. Each set of blades for a given stage may have its own disk. The vanes of the compressor section 12 may be mounted to a casing, which may extend circumferentially around the turbine engine 10. It should be understood that the representation of the compressor section 12 is merely schematic and that there may be any number of blades, vanes, and stages. Further, it is contemplated that there may be any number of other components within the compressor section 12.

[0025] Similar to the compressor section 12, the turbine section 16 may include a plurality of axially spaced stages, with each stage having a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary vanes. The turbine blades for a stage of the turbine section 16 may be mounted to disks, which are mounted to the drive shaft 18. Each set of blades for a given stage may have its own disk. The turbine section's vanes may be mounted to the casing in a circumferential manner. It should be noted that there may be any number of blades, vanes, and turbine stages, as the illustrated turbine section is merely a schematic representation. Further, it is contemplated that there may be any number of other components within the turbine section 16.

[0026] The combustion section 14 may be disposed in series between the compressor section 12 and the turbine section 16. The combustion section 14 may be fluidly coupled to at least a portion of the compressor section 12 and the turbine section 16 such that the combustion section 14 at least partially fluidly couples the compressor section 12 to the turbine section 16. As a non-limiting example, the combustion section 14 may be fluidly coupled to the HP compressor 24 at an upstream end of the combustion section 14 and to the HP turbine 26 at a downstream end of the combustion section 14.

[0027] During operation of the turbine engine 10, ambient or atmospheric air is drawn into the compressor section 12 via a fan (not shown) upstream of the compressor section 12, where it is compressed, defining pressurized air. The pressurized air may then flow into the combustion section 14, where it is mixed with fuel and ignited, thereby generating combustion gases. The HP turbine 26 extracts some work from these combustion gases, which drives the HP compressor 24. The combustion gases are exhausted to the LP turbine 28, which extracts additional work to drive the LP compressor 22, and the exhaust gases are ultimately exhausted from the turbine engine 10 via an exhaust section (not shown) downstream of the turbine section 16. The drive of the LP turbine 28 drives the LP spool, which rotates the fan (not shown) and the LP compressor 22. Together, the pressurized airflow and the combustion gases may define the working airflow flowing through the fan, compressor section 12, combustion section 14, and turbine section 16 of the turbine engine 10.

[0028] Figure 2 Describes the suitable Figure 1 1 is a cross-sectional view of a generic combustor 30 used in the combustion section 14 of FIG. The combustor 30 may include a fuel nozzle assembly 38 for providing fuel to the combustor 30. In some examples, the fuel nozzle assembly 38 may include fuel nozzles in an annular arrangement. It should be understood that the fuel nozzle assembly 38 may be organized in any suitable arrangement, pattern, grouping, etc. Depending on the type of engine in which the combustor 30 is located, the combustor 30 may have a can shape, a can annular shape, or an annular arrangement. The combustor 30 may also include a combustor liner 40. In some examples, the combustor liner 40 may have an annular structure about the combustor 30. In some examples, the combustor liner 40 may include multiple segments or portions that together form the combustor liner 40.

[0029] A dome assembly 44 may also be disposed in the combustor 30. The dome assembly 44 may include a dome 46 and a flow inducer 48. The combustor liner 40 and the dome assembly 44 may collectively at least partially define a combustion chamber 50 about a longitudinal axis 52. At least one fuel supply 54 may be fluidly coupled to the combustion chamber 50 to supply fuel to the combustor 30. In non-limiting examples, the fuel may include any suitable fuel, including a hydrocarbon fuel or a hydrogen fuel.

[0030] A fuel supply 54 may be disposed within the dome assembly 44 to define a general fuel outlet 56 to the combustion chamber 50. In some examples, a flared cone 58 may be disposed downstream of the fuel supply 54. A swirler 59 may also be disposed at the fuel nozzle assembly 38 to swirl incoming air about the fuel exiting the fuel supply 54 and provide a uniform mixture of air and fuel entering the combustor 30.

[0031] A set of dilution holes 60 may be provided in the combustor liner 40 and configured to direct air into the combustion chamber 50 for temperature control, flame shaping, fuel-air mixing, etc. Although a single dilution hole is shown, any number may be provided in the set of dilution holes 60. The set of dilution holes 60 may have any suitable pattern or arrangement on the combustor liner 40, including linear rows, irregular groups, variable hole diameters, etc., or combinations thereof.

[0032] Steering Figure 3 , showing that it can be in the combustion section 14 ( Figure 1 ) is a part of another burner 130 used in the burner 130. The burner 130 is connected to the burner 30 ( Figure 2 ) are similar; therefore, like parts will be described with like numerals increased by 100, and it should be understood that the description of like parts of burner 30 applies to burner 130 unless otherwise specified.

[0033] The combustor 130 may extend along a longitudinal axis 152 and include a fuel nozzle assembly 138, a combustor liner 140, an inducer 148, a combustion chamber 150, a fuel supply 154, and a set of dilution holes 160. In the illustrated example, the set of dilution holes 160 is schematically illustrated, with a dilution hole centerline (designated "C") shown extending through the combustor liner 140. It will be understood that the set of dilution holes 160 may form hollow apertures extending through the combustor liner 140. Such apertures may have any suitable geometric profile, including circular, elliptical, oval, symmetrical, asymmetrical, irregular, etc. For clarity, the set of dilution holes 160 is illustrated on an upper portion of the combustor liner 140. It will be understood that the set of dilution holes 160 may be provided on any portion of the combustor liner 140 and may also have any arrangement, number, or pattern, including in an annular arrangement about the combustor liner 140.

[0034] One difference compared to the combustor 30 is that the set of dilution holes 160 can have a variable axial spacing distance along the longitudinal axis 152. In one example, a first axial distance 161 is illustrated between a first pair of dilution holes 160A in the set of dilution holes 160, and a second axial distance 162 is illustrated between a second pair of dilution holes 160B in the set of dilution holes 160. In some examples, the second axial distance 162 can be greater than the first axial distance 161. The first pair of dilution holes 160A can be positioned axially forward of the second pair of dilution holes 160B. In some examples, the axial distance between adjacent dilution holes in the set of dilution holes 160 can continuously increase in a downstream direction through the combustor 30. It is also contemplated that at least one of the axial distance or the circumferential distance between adjacent dilution holes in the set of dilution holes 160 can be a predetermined amount relative to the diameter of the dilution holes in the set of dilution holes 160. In non-limiting examples, the axial distance or the circumferential distance between adjacent dilution holes can be greater than the dilution hole diameter, or twice the dilution hole diameter, or between 2 and 100 times the dilution hole diameter.

[0035] Another difference compared to the combustor 30 is that the set of dilution holes 160 may form a constant or varying angle relative to the combustor liner 140. One exemplary angle (denoted as "A") is indicated for the dilution holes in the set of dilution holes 160. In some examples, the angle A may be non-orthogonal to the longitudinal axis 152, including between 10-90 degrees.

[0036] Another difference compared to the combustor 30 is that the deflector 148 can have a flat or substantially flat geometric profile. The deflector 148 can also be comprised of a material having a high temperature capability. As used herein, the "temperature capability" of a material will refer to the maximum operating temperature for which the material is intended, where subjecting the material to temperatures above its temperature capability would result in effects such as oxidation, fatigue, plastic deformation, or melting of the material. In some examples, the deflector 148 can be comprised of a ceramic matrix composite (CMC) or a monolithic ceramic.

[0037] Another difference compared to combustor 30 is that fuel nozzle assembly 138 may include an air-fuel nozzle 170. In some examples, air-fuel nozzle 170 may include a body 171 having one or more nozzle outlets 172. In another non-limiting example, multiple air-fuel nozzles 170 may be provided, each air-fuel nozzle 170 having a body 171 with a single nozzle outlet 172. Any number of air-fuel nozzles 170 and nozzle outlets 172 may be provided. Nozzle outlets 172 may have any suitable arrangement within combustor 130.

[0038] The nozzle outlet 172 can be configured to inject both air and fuel into the combustion chamber 150. In the illustrated example, the air-fuel nozzle 170 includes a plurality of air flow channels 174 and fuel flow channels 175 extending through the body 171. The air flow channels 174 can at least partially surround the fuel flow channels 175. Each air flow channel 174 can extend between an air inlet 180 and an air outlet 182. Each fuel flow channel 175 can extend between a fuel inlet 184 and a fuel outlet 186. Each of the air outlet 182 and the fuel outlet 186 can be fluidly coupled to the combustion chamber 150. The air flow channels 174 and the fuel flow channels 175 can fluidly combine at the nozzle outlet 172 via the air outlet 182 and the fuel outlet 186. Additionally, the fuel outlet 186 can be positioned upstream of the downstream end of the body 171 relative to the longitudinal axis 152.

[0039] The air flow passage 174 may define an air passage width 174W. The fuel flow passage 175 may define a fuel passage width 175W. Either or both of the air passage width 174W, the fuel passage width 175W, or both may be constant or variable along the longitudinal axis 152. In one example, the air passage width 174W may decrease in size along at least a portion of the air flow passage 174 as one moves downstream along the longitudinal axis 152. In one example, the fuel passage width 175W may increase in size and then decrease in size as one moves downstream along the longitudinal axis 152.

[0040] At least one swirler may be disposed in at least one of the fuel flow passage 175 or the air flow passage 174 upstream of the nozzle outlet 172. In some examples, a fuel swirler 178 may be disposed in the fuel flow passage 175. In this case, the fuel swirler 178 may be configured to swirl the incoming fuel upstream of the nozzle outlet 172. In some examples, the incoming fuel may flow directly through the fuel flow passage 175 and into the combustion chamber 150 without the use of a fuel swirler (e.g., a fuel jet).

[0041] In some examples, an air swirler 176 may be disposed in the air flow passage 174. In this case, the air swirler 176 may be configured to swirl the incoming air upstream of the nozzle outlet 172. In some examples, the incoming air may flow directly through the air flow passage 174 and into the combustion chamber 150 without the use of an air swirler (e.g., an air jet).

[0042] Another difference compared to combustor 30 is that fuel can be supplied to fuel nozzle assembly 138 in multiple fuel supply conduits. In the illustrated example, fuel supply 154 includes a first fuel supply conduit 191 and a second fuel supply conduit 192, although any number of fuel supply conduits may be provided. First fuel supply conduit 191 can supply fuel to at least first fuel flow channel 175A, and second fuel supply conduit 192 can supply fuel to at least second fuel flow channel 175B. In the non-limiting example shown, first fuel supply conduit 191 can supply fuel to first fuel flow channel 175A, and second fuel supply conduit 192 can supply fuel to second fuel flow channel 175B and third fuel flow channel 175C. In some examples, first fuel supply conduit 191 and second fuel supply conduit 192 can supply fuel simultaneously or at different intervals. In other non-limiting examples, first fuel supply conduit 191 and second fuel supply conduit 192 can also supply the same fuel, different fuels, the same fuel mixture, or different fuel mixtures to fuel inlet 184.

[0043] In some examples, the controller can independently control the fuel supply to the first fuel supply conduit 191 and the second fuel supply conduit 192. Such independent control can include supplying separate fuel types, separate fuel flow rates, separate fuel supply timings, etc. to the first fuel supply conduit 191 and the second fuel supply 192. In one non-limiting example, a full authority digital engine controller (FADEC) can communicate signals with one or more fuel sources. The FADEC can controllably operate the one or more fuel sources to supply fuel to at least one of the first fuel supply conduit 191 or the second fuel supply conduit 192. In some non-limiting examples, the controller can also independently supply fuel to selected nozzle outlets 172 or to selected groups of nozzle outlets 172.

[0044] Figure 4 A top view of the combustor 130 is shown with a set of dilution holes 160 shown in further detail. It will be understood that the set of dilution holes 160 may include the same dilution holes, different dilution holes, the same subset of dilution holes, different subsets of dilution holes, and the like.

[0045] Some exemplary dilution hole centerlines C are indicated by dashed lines. It is further contemplated that, in some examples, the centerline C may be formed in a circumferential direction, such as to provide a swirling flow within the combustion chamber 150. In some examples, an angle A may also be formed in an axial direction along the longitudinal axis 152 and configured to reduce shear stress or mixing when air is introduced into the combustion chamber 150. In some examples, the angle A may be directed in a radially inward direction, such as to provide flame shaping or to direct fuel or flame away from the combustor liner 140.

[0046] In some examples, a set of dilution holes 160 may include a channel geometry having a cross-sectional area that decreases in a downstream direction to provide a rapid dilution jet entering the combustion chamber 150. An exemplary dilution hole 160C in the set of dilution holes 160 is shown as having a first cross-sectional area (designated as "C1") and a second cross-sectional area (designated as "C2"). Dashed arrows indicate the flow direction through the dilution hole 160C. The second cross-sectional area C2 may be smaller than the first cross-sectional area C1, thereby providing a decreasing cross-sectional area in the downstream direction within the dilution hole 160C.

[0047] Another exemplary dilution hole 160E in the set of dilution holes 160 is shown having its centerline C. The centerline C may form an angle A with the longitudinal axis 152 as shown. In some examples, the angle A may be between 10 and 90 degrees. It should also be understood that the angle A may be formed radially relative to the longitudinal axis 152, circumferentially about the longitudinal axis 152, or a combination thereof.

[0048] An exemplary pore diameter (denoted as "d H ”) is indicated for a dilution hole in the set of dilution holes 160. It is also contemplated that the set of dilution holes 160 may be elongated, elliptical, asymmetric, non-circular, etc. Another exemplary dilution hole 160D in the set of dilution holes 160 is shown as having an elliptical geometric profile. The dilution hole 160D may define a major diameter D (denoted as “D”) and a minor diameter d (denoted as “d”). In some non-limiting examples, the ratio of the major diameter D to the minor diameter d may be between 1-5, or between 1-3, or between 1-2.

[0049] The set of dilution holes 160 may also include a hole diameter configured to form a micro-dilution jet into the combustion chamber 150. In some examples, the set of dilution holes 160 may include micro-dilution jets formed by larger hole diameters than conventional combustors. In a non-limiting example, the hole diameter d HAny of the diameters d, major diameter D, or minor diameter d can be between 1 mm and 3 mm. Compared to the airflow through a single conventional dilution hole, such micro-dilution jets can have a relative airflow range of 0.01-0.25. In a non-limiting example, relative to the typical airflow through one conventional dilution hole in a conventional combustor, micro-dilution jets ranging from 4 to 100 micro-dilution holes in a group of dilution holes 160 can collectively form the same airflow. In some examples, the micro-dilution jets can also have a pressure drop of between 1% and 5% of the combustor inlet pressure.

[0050] The set of dilution holes 160 may be constructed, arranged, selected, etc. to allow the jet to penetrate into the combustion chamber 150. In one non-limiting example, the set of dilution holes 160 may allow the jet to penetrate 2-5 times the thickness of the boundary layer near the combustor liner 140. In this manner, during operation, the high-speed jet, larger diameter dilution holes, and greater pressure drop may create greater velocity momentum within the combustion chamber 150 and drive hydrogen away from the combustor liner 140.

[0051] Go to Figure 5 , viewed in the forward direction along the longitudinal axis 152, along Figure 3 Line VV shows a cross-sectional view of air-fuel nozzle 170. Air-fuel nozzle 170 is schematically shown in an exemplary configuration having ten bodies 171 arranged in an annular arrangement about longitudinal axis 152, with each body 171 including six nozzle outlets 172, although this need not be the case. Any number of bodies 171 and nozzle outlets 172 may be provided. In some examples, air-fuel nozzle 170 may include a single or unitary body 171 having multiple nozzle outlets 172. In some examples, air-fuel nozzle 170 may include multiple bodies 171, each having a single nozzle outlet 172. In some examples, air-fuel nozzle 170 may include multiple bodies 171 having different numbers of nozzle outlets 172. In some examples, nozzle outlets 172 may optionally be integrated into or integrally formed with air-fuel nozzle 170. In some examples, nozzle outlet 172 may also be located at the center of air-fuel nozzle 170.

[0052] Dividing wall 179 is shown as forming an annular air flow passage 174 that is separated from fuel flow passage 175. Any arrangement, shape, or positioning can be used for air flow passage 174 and fuel flow passage 175 to form nozzle outlet 172. Although air flow passage 174 and fuel flow passage 175 are generally shown as having circular cross-sections, in non-limiting examples, air flow passage 174 and fuel flow passage 175 can have any suitable geometric profile, including oval, square, annular, segmented, symmetrical, asymmetrical, or irregular. An exemplary air flow passage 174P is illustrated as having an elongated or oval geometric profile. An exemplary fuel flow passage 175P is illustrated as having a geometric profile with a non-constant channel width. Any geometric profile is contemplated.

[0053] Furthermore, the nozzle outlets 172 can be arranged circumferentially about the longitudinal axis 152. In some examples, the nozzle outlets 172 can also be arranged in multiple concentric rings. In the non-limiting example shown, the first nozzle outlet 172A can be circumferentially offset from the second nozzle outlet 172B. In other words, the first nozzle outlet 172A can be radially misaligned with the second nozzle outlet 172B relative to the longitudinal axis 152. In this manner, multiple nozzle outlets 172, multiple annular air flow passages 174, and multiple fuel flow passages 175 can be provided in the air-fuel nozzle 170.

[0054] Generally speaking Figure 3-5 During operation, fuel and air may be supplied to the air-fuel nozzle 170. Either or both of the supplied air or fuel may swirl along the air flow passage 174 and the fuel flow passage 175 upstream of the nozzle outlet 172. In this manner, fuel and air may be supplied, mixed, and injected into the combustion chamber 150 through multiple injection points in any suitable pattern or arrangement. Furthermore, air may be supplied to the combustion chamber 150 through a set of dilution holes 160. The set of dilution holes 160 may provide micro-dilution jets into the combustion chamber 150 in multiple directions, including axial, circumferential, or a combination thereof.

[0055] The above aspects provide multiple benefits, including multi-point injection of air and fuel into the combustion chamber. This multi-point injection can provide for shaping and positioning of the combustion flame within the combustion chamber. Furthermore, the micro-dilution jets formed by the larger diameter dilution holes provide higher velocity air entering the combustion chamber with a greater pressure drop. The micro-dilution jets formed by the dilution holes can have a greater velocity momentum to direct fuel away from the combustor liner and be used for temperature control or fuel mixing purposes. Furthermore, the micro-dilution jets described herein can also minimize fuel dispersion upstream of the liner.

[0056] Aspects of the present disclosure, including staged multi-point injection of fuel and air into the combustion chamber, can further provide for a reduced combustor length. In some examples, the combustor length can be reduced by 50% compared to conventional combustors.

[0057] Aspects of the present disclosure can further provide a reduction in combustor length compared to conventional combustors. In one example, the combustor length can be reduced by 50% compared to conventional combustors. Aspects of the present disclosure further provide an improved profile or pattern factor for the combustion gases entering the downstream turbine section. Front-mounted multi-point direct injection can use an annular combustor geometry for lean fuel-air mixtures to achieve reduced emissions (including NO x ) and improve mixing, thereby beneficially affecting the profile / pattern factor.

[0058] Furthermore, using a flat deflector with a high heat capacity material (such as CMC) can provide reduced hardware stress in the combustion environment. Shaped multi-holes on the deflector face can further increase the combustor's heat capacity. Fuel staging within the multi-point direct injection swirler can further help optimize engine operability and improve emissions control.

[0059] Although described with respect to a turbine engine, it should be understood that aspects of the present disclosure may have general applicability to any combustor. In non-limiting examples, aspects of the disclosure described herein may also be applicable to an engine having a propeller section, a fan, and a supercharger section, a turbojet engine, or a turboshaft engine.

[0060] To the extent not already described, the different features and structures of the various embodiments may be used in combination or substituted for one another as desired. The fact that a feature is not shown in all embodiments does not mean it cannot be shown in such a manner; rather, it is shown for the sake of brevity. Thus, various features of different embodiments may be mixed and matched as desired to form new embodiments, whether or not such new embodiments are explicitly described. All combinations or permutations of the features described herein are covered by this disclosure.

[0061] Further aspects of the present disclosure are provided by the following clauses:

[0062] 18. The ventilator as claimed in claim 15, wherein the ventilator is an airtight container and a fuel filter is provided to contact the ventilator of the fuel injection nozzle. The ventilator is a fuel filter which is provided to the fuel injector of the fuel injection nozzle. The ventilator is a fuel filter which is provided to the fuel injector of the fuel injection nozzle. The ventilator is a fuel filter which is provided to the fuel injector of the fuel injection nozzle.

[0063] A turbine engine according to any of the preceding clauses, wherein the at least one swirler comprises a fuel swirler located in the fuel flow channel.

[0064] Turbine engine according to any of the preceding clauses, wherein said at least one swirler comprises an air swirler located in said air flow channel.

[0065] Turbine engine according to any of the preceding clauses, wherein the at least one swirler comprises a fuel swirler located in the fuel flow channel, and an air swirler located in the air flow channel.

[0066] A turbine engine according to any of the preceding clauses, further comprising a second fuel flow passage extending through the body, and a second air flow passage annularly surrounding the second fuel flow passage and extending through the body.

[0067] The turbine engine according to any of the preceding clauses, further comprising a plurality of air flow passages extending through the body, and a plurality of fuel flow passages within the plurality of air flow passages.

[0068] The turbine engine according to any of the preceding clauses, wherein the fuel supply comprises a first fuel supply conduit and a second fuel supply conduit, wherein the first fuel supply conduit is fluidly coupled to the fuel flow passage and the second fuel supply conduit is fluidly coupled to a second fuel flow passage.

[0069] The turbine engine according to any of the preceding clauses, further comprising hydrogen fuel supplied to the fuel flow passage by the first fuel supply conduit, and hydrocarbon fuel supplied to the second fuel flow passage by the second fuel supply conduit.

[0070] The turbine engine according to any of the preceding clauses, further comprising a hydrogen fuel supplied by the first fuel supply conduit to one of the fuel flow passage or the second fuel flow passage, and a hydrocarbon fuel supplied by the second fuel supply conduit to the other of the fuel flow passage or the second fuel flow passage.

[0071] A turbine engine according to any of the preceding clauses, further comprising a plurality of nozzle outlets including the nozzle outlet.

[0072] A turbine engine according to any of the preceding clauses, further comprising a plurality of annular air flow channels comprising the air flow channel.

[0073] The turbine engine according to any of the preceding clauses, further comprising a plurality of fuel flow channels including the fuel flow channel and located within a corresponding plurality of air flow channels, wherein the plurality of nozzle outlets are arranged circumferentially about the body.

[0074] A turbine engine according to any of the preceding clauses, further comprising a plurality of nozzle outlets arranged circumferentially about the body.

[0075] The turbine engine of any of the preceding clauses, further comprising a first nozzle outlet and a second nozzle outlet, wherein the first nozzle outlet is radially misaligned with the second nozzle outlet relative to a longitudinal axis extending through the combustor.

[0076] The turbine engine according to any of the preceding clauses, further comprising a plurality of bodies including a plurality of nozzle outlets having a corresponding plurality of air flow channels, and further comprising a plurality of fuel flow channels within the corresponding plurality of air flow channels.

[0077] The turbine engine according to any of the preceding clauses, further comprising a set of dilution holes in the combustor liner, wherein a first pair of adjacent dilution holes in the set of dilution holes are spaced apart to define a first axial distance relative to a longitudinal axis extending through the combustor, and wherein a second pair of adjacent dilution holes in the set of dilution holes are spaced apart to define a second axial distance relative to the longitudinal axis, wherein the second axial distance is greater than the first axial distance.

[0078] A turbine engine according to any of the preceding clauses, wherein the first pair of adjacent dilution holes is positioned axially forward of the second pair of adjacent dilution holes relative to the longitudinal axis.

[0079] A turbine engine according to any of the preceding clauses, wherein the dilution holes in the set of dilution holes define a major diameter and a minor diameter, wherein the minor diameter is smaller than the major diameter.

[0080] The turbine engine according to any of the preceding clauses, wherein the dilution holes of the set of dilution holes define an angle relative to the longitudinal axis, wherein the angle is between 10-90 degrees.

[0081] Turbine engine according to any of the preceding clauses, wherein the dilution holes of the set of dilution holes comprise a cross-sectional area that decreases in a downstream direction.

[0082] The turbine engine according to any of the preceding clauses, further comprising an inducer having a flat geometric profile in the combustor.

[0083] Turbine engine according to any of the preceding clauses, wherein the inducer comprises a material having high temperature capability.

[0084] The turbine engine according to any of the preceding clauses, wherein the inducer comprises at least one of a ceramic or a ceramic matrix composite material.

[0085] A turbine engine comprising a compressor section, a combustion section, and a turbine section in a serial flow arrangement, the combustion section having a combustor including a combustor liner at least partially defining a combustion chamber, and a set of dilution holes within the combustor liner, wherein a first pair of adjacent dilution holes in the set of dilution holes are spaced apart to define a first axial distance relative to a longitudinal axis extending through the combustor, and wherein a second pair of adjacent dilution holes in the set of dilution holes are spaced apart to define a second axial distance relative to the longitudinal axis, wherein the second axial distance is greater than the first axial distance.

[0086] A turbine engine according to any of the preceding clauses, wherein the first pair of adjacent dilution holes is positioned axially forward of the second pair of adjacent dilution holes relative to the longitudinal axis.

[0087] A turbine engine according to any of the preceding clauses, wherein the dilution holes in the set of dilution holes define a major diameter and a minor diameter, wherein the minor diameter is smaller than the major diameter.

[0088] Turbine engine according to any of the preceding clauses, wherein the dilution holes of the set of dilution holes define an angle relative to the longitudinal axis, said angle being between 10-90 degrees.

[0089] Turbine engine according to any of the preceding clauses, wherein the dilution holes of the set of dilution holes comprise a cross-sectional area that decreases in a downstream direction.

[0090] 19. The combustor of claim 18, wherein the vents of the combustor are configured to extend through a channel formed between a first end of and a second end of the diverter tube, the channel having a central portion for receiving the vents and a central portion for receiving the vents. The vents of the combustor are configured to extend through a channel formed between a first end of and a second end of the diverter tube, the channel having a central portion for receiving the vents and the central portion for receiving the vents.

[0091] A combustor according to any of the preceding clauses, wherein the at least one swirler comprises a fuel swirler located in the fuel flow channel.

[0092] A burner according to any of the preceding clauses, wherein the at least one swirler further comprises an air swirler located in the air flow channel.

[0093] A combustor according to any of the preceding clauses, wherein the at least one swirler comprises a fuel swirler located in the fuel flow channel.

[0094] A burner according to any of the preceding clauses, wherein the at least one swirler comprises an air swirler located in the air flow channel.

[0095] A burner according to any of the preceding clauses, further comprising a second fuel flow passage extending through the body, and a second air flow passage annularly surrounding the second fuel flow passage and extending through the body.

[0096] The burner of any of the preceding clauses, wherein the fuel supply comprises a first fuel supply conduit and a second fuel supply conduit, wherein the first fuel supply conduit is fluidly coupled to the fuel flow passage and the second fuel supply conduit is fluidly coupled to the second fuel flow passage.

[0097] The burner according to any of the preceding clauses, further comprising hydrogen fuel supplied to the fuel flow passage by the first fuel supply conduit, and hydrocarbon fuel supplied to the second fuel flow passage by the second fuel supply conduit.

[0098] The burner according to any of the preceding clauses, further comprising a hydrogen fuel supplied by the first fuel supply conduit to one of the fuel flow channel or the second fuel flow channel, and a hydrocarbon fuel supplied by the second fuel supply conduit to the other of the fuel flow channel or the second fuel flow channel.

[0099] The combustor according to any of the preceding clauses further comprises: a plurality of nozzle outlets including the nozzle outlet, a plurality of annular air flow channels including the air flow channel, and a plurality of fuel flow channels including the fuel flow channel and located within the corresponding plurality of air flow channels, wherein the plurality of nozzle outlets are arranged circumferentially with respect to the body.

[0100] A combustor according to any of the preceding clauses, further comprising a plurality of nozzle outlets arranged circumferentially about the body.

[0101] The combustor of any of the preceding clauses, further comprising a first nozzle outlet and a second nozzle outlet, wherein the first nozzle outlet is radially misaligned with the second nozzle outlet relative to a longitudinal axis extending through the combustor.

[0102] The combustor of any of the preceding clauses, further comprising a set of dilution holes in the combustor liner, wherein a first pair of adjacent dilution holes in the set of dilution holes are spaced apart to define a first axial distance relative to a longitudinal axis extending through the combustor, and wherein a second pair of adjacent dilution holes in the set of dilution holes are spaced apart to define a second axial distance relative to the longitudinal axis, wherein the second axial distance is greater than the first axial distance.

[0103] The combustor of any of the preceding clauses, wherein the first pair of adjacent dilution holes are positioned axially forward of the second pair of adjacent dilution holes relative to the longitudinal axis.

[0104] The burner of any of the preceding clauses, wherein the dilution holes in the set of dilution holes define a major diameter and a minor diameter, wherein the minor diameter is smaller than the major diameter.

[0105] The burner of any of the preceding clauses, wherein the dilution holes of the set of dilution holes define an angle relative to the longitudinal axis, wherein the angle is between 10-90 degrees.

[0106] The combustor according to any of the preceding clauses, wherein the dilution holes of the set of dilution holes comprise a cross-sectional area that decreases in a downstream direction.

[0107] The burner according to any of the preceding clauses, further comprising a flow director having a flat geometric profile.

[0108] The burner of any of the preceding clauses, wherein the deflector comprises a material having high temperature capability.

[0109] The burner of any of the preceding clauses, wherein the flow director comprises at least one of a ceramic or a ceramic matrix composite material.

[0110] A combustor for a turbine engine includes a combustor liner at least partially defining a combustion chamber, and a set of dilution holes in the combustor liner, wherein a first pair of adjacent dilution holes in the set of dilution holes are spaced apart to define a first axial distance relative to a longitudinal axis extending through the combustor, and wherein a second pair of adjacent dilution holes in the set of dilution holes are spaced apart to define a second axial distance relative to the longitudinal axis, wherein the second axial distance is greater than the first axial distance.

[0111] The combustor of any of the preceding clauses, wherein the first pair of adjacent dilution holes are positioned axially forward of the second pair of adjacent dilution holes relative to the longitudinal axis.

[0112] The burner of any of the preceding clauses, wherein the dilution holes in the set of dilution holes define a major diameter and a minor diameter, wherein the minor diameter is smaller than the major diameter.

[0113] The burner of any of the preceding clauses, wherein the dilution holes of the set of dilution holes define an angle relative to the longitudinal axis, wherein the angle is between 10-90 degrees.

[0114] The combustor according to any of the preceding clauses, wherein the dilution holes of the set of dilution holes comprise a cross-sectional area that decreases in a downstream direction.

Claims

1. A turbine engine defining a longitudinal axis, characterized in that The turbine engine comprises: A compressor section, a combustion section, and a turbine section in a serial flow arrangement, with the combustion section having a combustor comprising: a combustor liner at least partially defining a combustion chamber; a flow deflector coupled to the combustor liner; a fuel supply fluidly coupled to the combustion chamber; and A group of fuel nozzle assemblies arranged as a first ring of fuel nozzle assemblies radially spaced from a second ring of fuel nozzle assemblies relative to the longitudinal axis, wherein each fuel nozzle assembly in the group of fuel nozzle assemblies comprises: a body having a nozzle outlet disposed on the inducer and fluidly coupled to the combustion chamber; an air flow passage located within the body and having an air outlet at least partially defining the nozzle outlet; and a fuel flow passage located within the air flow passage and having a fuel outlet at least partially defining the nozzle outlet; and wherein the group of fuel nozzle assemblies in the first ring of fuel nozzle assemblies is radially misaligned with the second ring of fuel nozzle assemblies.

2. The turbine engine according to claim 1, characterized in that The fuel supply includes a first fuel supply conduit and a second fuel supply conduit, wherein the first fuel supply conduit is fluidly coupled to the fuel flow passage and the second fuel supply conduit is fluidly coupled to the second fuel flow passage.

3. The turbine engine according to claim 2, characterized in that Further included is a hydrogen fuel supplied to one of the fuel flow passage or the second fuel flow passage by the first fuel supply conduit, and a hydrocarbon fuel supplied to the other of the fuel flow passage or the second fuel flow passage by the second fuel supply conduit.

4. The turbine engine according to claim 1, characterized in that Further comprising a set of dilution holes in the combustor liner, wherein the dilution holes in the set of dilution holes define an angle relative to a combustor longitudinal axis extending through the combustor, wherein the angle is between 10-90 degrees.

5. The turbine engine according to claim 1, characterized in that Further included is a set of dilution holes in the combustor liner, wherein the dilution holes in the set of dilution holes include a cross-sectional area that decreases in a downstream direction.

6. The turbine engine according to claim 1, characterized in that Further included is a set of dilution holes in the combustor liner, wherein the dilution holes in the set of dilution holes define a major diameter and a minor diameter, wherein the minor diameter is smaller than the major diameter.

7. The turbine engine according to claim 1, characterized in that Further comprising a set of dilution holes in the combustor liner, wherein a first pair of adjacent dilution holes in the set of dilution holes are spaced apart to define a first axial distance relative to a combustor longitudinal axis extending through the combustor, and wherein a second pair of adjacent dilution holes in the set of dilution holes are spaced apart to define a second axial distance relative to the longitudinal axis, wherein the second axial distance is greater than the first axial distance.

8. The turbine engine according to claim 7, characterized in that Wherein the first pair of adjacent dilution holes are positioned axially forward of the second pair of adjacent dilution holes relative to the longitudinal axis.

9. A combustor for a turbine engine, the turbine engine defining a longitudinal axis, characterized in that The burner comprises: a combustor liner at least partially defining a combustion chamber; a fuel supply fluidly coupled to the combustion chamber; and A fuel nozzle assembly comprising a set of nozzle outlets axially aligned relative to the longitudinal axis, wherein each nozzle outlet in the set of nozzle outlets comprises: a body having a nozzle outlet fluidly coupled to the combustion chamber; an air flow passage within the body and having an air outlet fluidly coupled to the nozzle outlet; and a fuel flow passage within the air flow passage and having a fuel outlet fluidly coupled to the nozzle outlet; and The set of nozzle outlets are circumferentially arranged about the longitudinal axis in a first ring radially spaced from a second ring, wherein at least some nozzle outlets in the first ring radially overlap and are radially non-aligned with at least some nozzle outlets in the second ring.

10. The burner according to claim 9, characterized in that The fuel supply portion includes a first fuel supply conduit and a second fuel supply conduit, and at least one of the first fuel supply conduit and the second fuel supply conduit supplies hydrogen fuel.

11. The burner according to claim 9, characterized in that Further included is a set of dilution holes in the combustor liner, wherein the dilution holes in the set of dilution holes include a cross-sectional area that decreases in a downstream direction.

12. The burner according to claim 9, characterized in that Further comprising a set of dilution holes in the combustor liner, wherein a first pair of adjacent dilution holes in the set of dilution holes are spaced apart to define a first axial distance relative to a longitudinal axis extending through the combustor, and wherein a second pair of adjacent dilution holes in the set of dilution holes are spaced apart to define a second axial distance relative to the longitudinal axis, wherein the second axial distance is greater than the first axial distance.

13. The burner according to claim 12, characterized in that Wherein the first pair of adjacent dilution holes are positioned axially forward of the second pair of adjacent dilution holes relative to the longitudinal axis.

Images