Turbine engine combustor and combustor liner

Abstract

A turbine engine can include a compressor section, a combustion section, and a turbine section in a serial flow arrangement. A combustor in the combustion section can include a combustor liner at least partially defining a combustion chamber. The combustor liner can include at least one orifice fluidly coupled to the combustion chamber.

Description

[0001] Cross-references to related applications

[0002] This application claims the benefit of U.S. Provisional Patent Application No. 63 / 321,900, filed March 21, 2022, the entire contents of which are incorporated herein by reference. Technical Field

[0003] This subject matter generally relates to combustors with combustor bushings for turbine engines, and more specifically, to combustor bushings with dilution hole arrangements. Background Technology

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

[0005] In a typical turbine engine, air and fuel are supplied to the combustion chamber, mixed, and then ignited to produce hot gases. These hot gases are then fed into the turbine, where they cause the turbine to rotate and generate power. Attached Figure Description

[0006] In the attached image:

[0007] Figure 1 This is a schematic cross-sectional view of a turbine engine having a compression section, a combustion section, and a turbine section, based on the various aspects described herein.

[0008] Figure 2 It is based on the various aspects described in this article. Figure 1 A cross-sectional view of the combustion zone along line II-II.

[0009] Figure 3 It is along Figure 2 The cross-sectional view of line III-III shows the burner according to the various aspects described herein.

[0010] Figure 4 It includes burner bushings that can be used according to the various aspects described herein. Figure 1 A cross-sectional view of another burner of the turbine engine.

[0011] Figure 5 yes Figure 4 A cross-sectional view of the burner, showing the fluid flow.

[0012] Figure 6 It shows Figure 4 A top view of the burner bushing.

[0013] Figure 7 It is another burner bushing that includes the aspects described in this document and can be used Figure 1 A cross-sectional view of another burner of the turbine engine.

[0014] Figure 8 It shows Figure 7 A top view of the burner bushing. Detailed Implementation

[0015] The aspects of this disclosure described herein relate to combustors with combustor bushings. 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 combustors 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.

[0016] 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.

[0017] 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.

[0018] The terms "front" and "rear" refer to relative positions within a gas turbine engine or vehicle, and specifically to the normal operating posture of the gas turbine engine or vehicle. For example, in the case of a gas turbine engine, "front" refers to the position closer to the engine inlet, while "rear" refers to the position closer to the engine nozzle or exhaust port.

[0019] As used herein, the term "upstream" refers to the direction opposite to the direction of fluid flow, while the term "downstream" refers to the direction in the same direction as the fluid flow. The terms "front" or "in front" indicate what is in front of something, and "rear" or "behind" indicate what is behind something. For example, when used in relation to fluid flow, "front" / "in front" can refer to upstream, and "rear" / "behind" can refer to downstream.

[0020] The term "fluid" can refer to either a gas or a liquid. The term "fluid connectivity" means that fluids can establish connections between specified areas.

[0021] Furthermore, as may be used herein, the term "radial" or "radially" refers to a direction away from the common center. For example, in the overall context of a turbine engine, radial refers to the direction along a ray extending between the engine's central longitudinal axis and the engine's outer perimeter.

[0022] All directional references (e.g., radial, axial, proximal, distal, up, down, upward, downward, left, right, lateral, front, rear, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, backward, etc.) are used for identification purposes only to aid the reader in understanding this disclosure and do not create limitation, particularly regarding the location, orientation, or use of aspects of the disclosure described herein. Connecting references (e.g., attachment, connection, joint, and engagement) are to be interpreted broadly and may include intermediate structural elements between sets of elements and relative movement between elements, unless otherwise indicated. Therefore, a connecting reference does not necessarily mean that two elements are directly connected and fixed relative to each other. Exemplary figures are for illustrative purposes only, and the dimensions, positions, order, and relative sizes reflected in the accompanying figures may vary.

[0023] The singular forms “a,” “an,” and “the” include plural references unless the context clearly indicates otherwise. Furthermore, as used herein, the term “group” or “set” of elements can be any number of elements, including only one.

[0024] As used herein and throughout the specification and claims, approximate language is applied to modify any quantitative representation that may allow for variation without altering its associated essential function. Therefore, values ​​modified by one or more terms such as “about,” “approximately,” “substantially,” and “basically” are not limited to the specified precise values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value, or the precision of the method or machine used to construct or manufacture the component and / or system. For example, approximate language may refer to a margin of 1%, 2%, 4%, 5%, 10%, 15%, or 20% of the endpoints of a single value, a range of values, and / or a range of defined values. Scope limitations are combined and interchanged herein and throughout the specification and claims; such scope is identified and includes all subscopes contained herein, unless otherwise indicated by context or language. For example, all scopes disclosed herein include endpoints, and endpoints can be combined independently of each other.

[0025] Figure 1This is a schematic diagram of a turbine engine 10. As a non-limiting example, the turbine engine 10 can be used within an aircraft. The turbine engine 10 may include at least a compressor section 12, a combustion section 14, and a turbine section 16. A drive shaft 18 rotatably connects the compressor section 12 and the turbine section 16 such that rotation of one affects rotation of the other, and defines the rotation axis 20 of the turbine engine 10.

[0026] Compressor section 12 may include a low-pressure (LP) compressor 22 and a high-pressure (HP) compressor 24 that are fluidly connected in series with each other. Turbine section 16 may include an HP turbine 26 and an LP turbine 28 that are fluidly connected in series with each other. Drive shaft 18 may operatively connect the LP compressor 22, HP compressor 24, HP turbine 26, and LP turbine 28 together. Alternatively, drive shaft 18 may include an LP drive shaft (not shown) and an HP drive shaft (not shown). The LP drive shaft may connect the LP compressor 22 to the LP turbine 28, and the HP drive shaft may connect the HP compressor 24 to the HP turbine 26. The LP spool may be defined as a combination of the LP compressor 22, LP turbine 28, and LP drive shaft, such that rotation of the LP turbine 28 may apply a driving force to the LP drive shaft, which in turn may rotate the LP compressor 22. The HP spool may be defined as a combination of the HP compressor 24, HP turbine 26, and HP drive shaft, such that rotation of the HP turbine 26 may apply a driving force to the HP drive shaft, which in turn may rotate the HP compressor 24.

[0027] Compressor section 12 may include multiple axially spaced stages. Each stage includes a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary blades. Compressor blades for a stage of compressor section 12 may be mounted to a disc, which is mounted to drive shaft 18. Each set of blades for a given stage may have its own disc. The blades of compressor section 12 may be mounted to a housing that may extend circumferentially around turbine engine 10. It should be understood that the representation of compressor section 12 is merely illustrative and any number of blades, blades, and stages may be possible. Furthermore, it is contemplated that any number of other components may be present within compressor section 12.

[0028] Similar to compressor section 12, turbine section 16 may include multiple axially spaced stages, each stage having a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary blades. Turbine blades for one stage of turbine section 16 may be mounted to a disc, which is mounted to drive shaft 18. Each set of blades for a given stage may have its own disc. The blades of the turbine section may be circumferentially mounted to the housing. It should be noted that any number of blades, blades, and turbine stages can be present, as the illustrated turbine section is merely schematic. Furthermore, it is contemplated that any number of other components may be present within turbine section 16.

[0029] Combustion section 14 may be arranged in series between compressor section 12 and turbine section 16. Combustion section 14 may be fluidly coupled to at least a portion of compressor section 12 and turbine section 16, such that combustion section 14 at least partially fluidly couples compressor section 12 to turbine section 16. As a non-limiting example, combustion section 14 may be fluidly coupled to HP compressor 24 at its upstream end and to HP turbine 26 at its downstream end.

[0030] 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.

[0031] Figure 2 Depicting along Figure 1The image shows a cross-sectional view of combustion section 14 along line II-II. Combustion section 14 may include a 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. 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 engine housing 29.

[0032] 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 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.

[0033] Figure 3 Depicting along Figure 2 The cross-sectional view taken along line III-III shows the burner 30. The burner 30 may include a fuel nozzle assembly 38 for supplying fuel to the burner 30. In some examples, the fuel nozzle assembly 38 may include an annular arrangement of fuel nozzles. It should be understood that the fuel nozzle assembly 38 can be organized in any suitable arrangement, pattern, grouping, etc. Depending on the type of engine in which the burner 30 is located, the burner 30 may have a canister-shaped, canister-annular, or annular arrangement. In some examples, the fuel injector 31 ( Figure 2 It can be integrated into the fuel nozzle assembly 38.

[0034] The burner 30 may also include a burner bushing 40. 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 collectively form the burner bushing 40. In some examples, the burner bushing 40 may include an outer liner 41 that is radially spaced from the inner liner 42. In some examples, the burner bushing 40 may include a single bushing.

[0035] The dome assembly 44 may also be disposed within the burner 30. The dome assembly 44 may include a shroud 46 and a deflector 48. The burner bushing 40 and the dome assembly 44 may jointly define a combustion chamber 50 at least partially around a longitudinal axis 52. At least one fuel supply 54 may be fluidly coupled to the combustion chamber 50 to supply fuel to the burner 30. In a non-limiting example, the fuel may include any suitable fuel, including hydrocarbon fuels or hydrogen fuel.

[0036] Fuel supply 54 may be disposed within dome assembly 44 to define fuel outlet 56. In some examples, flared cone 58 may be disposed downstream of fuel supply 54. Swirler 59 may also be disposed at fuel nozzle assembly 38 to cause incoming air to swirl near fuel exiting fuel supply 54 and to provide a homogeneous mixture of air and fuel entering burner 30.

[0037] A set of dilution orifices 60 may be provided in the burner bushing 40 and configured to divert compressed air from the HP compressor 24 ( Figure 1 The dilution orifice is guided into the combustion chamber 50 for temperature control, flame shaping, fuel-air mixing, etc. Although a single dilution orifice is shown, for the purposes of this specification and its novel burners, any number of dilution orifices can be provided in this set of dilution orifices 60.

[0038] Turning Figure 4 This shows that it can be used in combustion section 14 ( Figure 1 This is a part of another burner 130 in the combustion chamber. Burner 130 is similar to burner 30; therefore, similar parts will be described with similarity figures increased by 100, and it should be understood that, unless otherwise stated, the description of similar parts of burner 30 applies to burner 130. Burner 130 has many novel aspects relating to the type and arrangement of dilution orifices and the corresponding structure, which makes it well-suited for burning gaseous fuels with a molecular density lower than air, such as hydrogen.

[0039] The burner 130 may include a burner bushing 140, a dome assembly 144, a combustion chamber 150, and a set of dilution orifices 160. The set of dilution orifices 160 may include one or more cooling orifices in the burner bushing 140, configured to direct compressed air into the combustion chamber 150. As shown, the burner 130 may also define a longitudinal axis or burner axis 152.

[0040] One difference compared to burner 30 is that the set of dilution orifices 160 may include multiple discrete or continuous orifices in burner bushing 140. The set of dilution orifices 160 may include any number of dilution orifices, openings, etc. The set of dilution orifices 160 may be located on any part of burner bushing 140. Figure 4In the example, the set of dilution orifices 160 is schematically shown as having rectangular openings or orifices. However, the set of dilution orifices 160 can have any suitable orifice profile, size, pattern, arrangement, or number on the burner bushing 140, including circular orifices, elongated orifices, extended grooves, linear rows, irregular groups, annular arrangements around the burner bushing 140, variable or constant orifice diameters, variable or constant groove widths, etc., or combinations thereof.

[0041] In the illustrated example, although any number of orifices may be provided, the set of dilution orifices 160 may include a first orifice 161, a second orifice 162, and a third orifice 163. Furthermore, in the illustrated example, the first orifice 161, the second orifice 162, and the third orifice 163 may include one or more grooves extending at least partially around the burner bushing 140 in the circumferential direction.

[0042] Another difference from burner 30 is that burner bushing 140 may include a set of protruding walls or grilles configured to project into combustion chamber 150. In some examples, such protruding walls or grilles may be positioned adjacent to some of the dilution orifices in the set of dilution orifices 160. Furthermore, in some examples, it is envisioned that such protruding walls or grilles may optionally include orifices for airflow.

[0043] In the non-limiting example shown, the first fence wall 171, the second fence wall 172, and the third fence wall 173 are respectively positioned downstream of the respective first orifice 161, second orifice 162, and third orifice 163. In some examples, the first fence wall 171, the second fence wall 172, or the third fence wall 173 may be positioned directly downstream of, spaced apart from, or at least partially overlapped with the respective first orifice 161, second orifice 162, and third orifice 163. In some examples, the burner 130 may comprise only a single wall or fence. In some examples, the burner 130 may comprise more than three walls or fences.

[0044] In a non-limiting example where the burner bushing 140 includes an outer liner and an inner liner, the first grid wall 171, the second grid wall 172, and the third grid wall 173 may protrude from the inner liner. In another non-limiting example where the burner bushing 140 includes a single bushing, the first grid wall 171, the second grid wall 172, and the third grid wall 173 may protrude from the single bushing.

[0045] As shown in the figure, the dome height 180 can be defined within the burner 130. Furthermore, the first grid wall 171, the second grid wall 172, and the third grid wall 173 can define corresponding first heights 181, second heights 182, and third heights 183. The first heights 181, second heights 182, and third heights 183 can have any suitable dimensions. In a non-limiting example, any one of the first, second, or third heights 181, 182, 183 can be between 1 mm and 30 mm.

[0046] The first height 181, the second height 182, and the third height 183 can also have any suitable dimensions relative to each other. For example, the first height 181 can be equal to, greater than, or less than the second height 182. The second height 182 can be equal to, greater than, or less than the third height 183. The first height 181 can be equal to, greater than, or less than the third height 183. In the non-limiting example shown, the first height 181 is less than the second height 182 and the third height 183, and the third height 183 is less than the second height 182.

[0047] Further envisioning, any one of the first fence wall 171, the second fence wall 172, or the third fence wall 173 may have a variable length in the circumferential direction around the burner 30. Additionally or alternatively, the first fence wall 171, the second fence wall 172, or the third fence wall 173 may include multiple discrete or separate segments that collectively form a wall. In the illustrated example, compared to the corresponding first, second, and third heights 181, 182, 183, at another portion of the burner 130 (e.g., at another portion of the burner bushing 140), the first fence wall 171 includes a fourth height 184, the second fence wall 172 includes a fifth height 185, and the third fence wall 173 includes a sixth height 186. The fourth height 184 may be equal to, greater than, or less than the first height 181. The fifth height 185 may be equal to, greater than, or less than the second height 182. The sixth height 186 may be equal to, greater than, or less than the third height 183.

[0048] The first, second, third, fourth, fifth, and sixth heights 181, 182, 183, 184, 185, and 186 may also have predetermined ratios relative to each other or relative to the dome height 180. In some non-limiting examples: the ratio of the first height 181 to the fourth height 184 may be 0.1-5; the ratio of the second height 182 to the fifth height 185 may be 0.1-5; the ratio of the third height 183 to the sixth height 186 may be 0.1-5; the first height 181 may be 0.005-0.2 times the dome height 180; the ratio of the second height 182 to the first height 181 may be 0-15; the ratio of the fifth height 185 to the fourth height 184 may be 0-15; the ratio of the third height 183 to the first height 181 may be 0-15; or the ratio of the sixth height 186 to the first height 181 may be 0-15.

[0049] As shown in the figure, the burner 130 can also define a burner length 190. Furthermore, as shown, the first grid wall 171, the second grid wall 172, and the third grid wall 173 can define corresponding first lengths 191, second lengths 192, and third lengths 193 in the first portion of the burner 130 along the axial direction. The first length 191 can be defined relative to the dome assembly 144 along the burner axis 152. The second length 192 can be defined between the first grid wall 171 and the second grid wall 172. The third length 193 can be defined between the second grid wall 172 and the third grid wall 173.

[0050] As shown, the first grid wall 171, the second grid wall 172, and the third grid wall 173 may also define corresponding fourth lengths 194, fifth lengths 195, and sixth lengths 196 in a second portion of the burner 130 (e.g., at another portion of the burner bushing 140). The fourth length 194 may be defined relative to the dome assembly 144 along the burner axis 152. The fifth length 195 may be defined between the first grid wall 171 and the second grid wall 172. The sixth length 196 may be defined between the second grid wall 172 and the third grid wall 173.

[0051] The first, second, third, fourth, fifth, and sixth lengths 191, 192, 193, 194, 195, and 196 may also have predetermined ratios relative to each other or relative to the burner length 190. In some non-limiting examples: the first length 191 may be 0.01-0.2 times the burner length 190; the fourth length 194 may be 0.01-0.2 times the burner length 190; the second length 192 may be 0.1-0.6 times the burner length 190; the fifth length 195 may be 0.1-0.6 times the burner length 190; the third length 193 may be 0.1-0.7 times the burner length 190; the sixth length 196 may be 0.1-0.7 times the burner length 190; the first length 191 and the fourth length 194 may be of the same size or have different sizes; the fifth length 195 may be greater than, less than, or equal to the second length 192; or the sixth length 196 may be greater than, less than, or equal to the third length 193.

[0052] Furthermore, as shown in the figure, the first orifice 161 may define a first orifice distance 161D relative to the dome assembly 144. The first orifice distance 161D may be defined between the leading edge of the dome assembly 144 and the first orifice 161. In a non-limiting example, the first orifice distance 161D may be between 0.01 and 0.2 times the burner length 190.

[0053] The second orifice 162 may define a second orifice distance 162D relative to the first orifice 161. The second orifice distance 162D may be defined between the trailing edge of the first orifice 161 and the leading edge of the second orifice 162. In a non-limiting example, the second orifice distance 162D may be between 0.1 and 0.6 times the burner length 190.

[0054] The third orifice 163 may define a third orifice distance 163D relative to the second orifice 162. The third orifice distance 163D may be defined between the trailing edge of the second orifice 162 and the leading edge of the third orifice 163. In a non-limiting example, the third orifice distance 163D may be between 0.1 and 0.7 times the burner length 190.

[0055] Figure 5Some exemplary flow paths through combustion chamber 150 are shown. Some exemplary combustion flows C are shown within combustion chamber 150. First jet J1, second jet J2, and third jet J3 are shown entering combustion chamber 150 through corresponding first orifice 161, second orifice 162, and third orifice 163. During operation, first orifice 161 may be configured to guide first jet J1 such that combustion flow C, or combustion flame, is away from burner bushing 140 in the region near dome assembly 144. First grid wall 171, second grid wall 172, and third grid wall 173 may be configured to guide corresponding jets J1, J2, and J3 to the center of combustion chamber 150. In this way, first grid wall 171, second grid wall 172, and third grid wall 173 can control the penetration of airflow jets through this set of dilution orifices 160 to obtain a desired flame structure, and to reduce or at least partially extinguish the flame in the core of burner 130 with lower turbulence. In this way, the set of dilution orifices 160, the first fence wall 171, the second fence wall 172, and the third fence wall 173 can be configured to guide the dilution jets J1, J2, J3 into the combustion chamber 150, reduce the core temperature, and form or shape the desired outlet profile and mode factor for the combustion gas flow leaving the burner 130.

[0056] It is also conceivable that the amount of air entering the combustion chamber 150 can vary across the set of dilution orifices 160, including variations between the first orifice 161, the second orifice 162, and the third orifice 163. In some non-limiting examples: the first jet J1 can be greater than, less than, or equal to the second jet J2; the second jet J2 can be greater than, less than, or equal to the third jet J3; the first jet J1 can have 1-20% of the total dilution flow through the set of dilution orifices 160; the third jet J3 can have 0-40% of the total dilution flow through the set of dilution orifices 160; or the second jet J2 can have 80-100% of the total dilution flow through the set of dilution orifices 160. It should be understood that the first, second, and third jets J1, J2, and J3 can have any relative dimensions to each other. In this way, the first, second, and third jets J1, J2, and J3 can achieve the desired splitting through this set of dilution orifices 160, providing lower NO levels. x The exhaust gas is shaped to the desired temperature distribution of the combustion gases leaving the burner 130, and the combustion flame is moved away from the burner bushing 140 to improve durability.

[0057] In a non-limiting example using hydrogen fuel, the first orifice 161 can guide a light hydrogen and air mixture away from the burner bushing 140 via a first jet J1. The second and third orifices 162, 163, and walls 171, 172, 173 can introduce additional compressor air and further guide the light hydrogen and air mixture to the center of the combustion chamber 150, thereby providing a combustion gas flow shaped through the grid walls 171, 172, 173 and keeping the combustion flame away from the burner bushing 140 as described above.

[0058] Figure 6 A schematic top view of a portion of a burner bushing 140 is shown, illustrating the set of dilution orifices 160 (including a first orifice 161, a second orifice 162, and a third orifice 163) and a first grid wall 171, a second grid wall 172, and a third grid wall 173. Although only a portion is shown, it should be understood that the burner bushing 140 may be arranged in a ring, with the grid walls, slots, and orifices arranged in a similar ring configuration.

[0059] As shown in the figure, the first aperture 161, the second aperture 162, and the third aperture 163 can define corresponding first aperture widths 167, second aperture widths 168, and third aperture widths 169. Furthermore, as shown in the figure, the first fence wall 171, the second fence wall 172, and the third fence wall 173 can define corresponding first fence wall widths 177, second fence wall widths 178, and third fence wall widths 179. The first aperture widths 167, second aperture widths 168, third aperture widths 169, first fence wall widths 177, second fence wall widths 178, and third fence wall widths 179 can have any suitable dimensions, including any relative dimensions to each other. In some non-limiting examples, the first aperture width 167, the second aperture width 168, or the third aperture width 169 can be between 0.5 mm and 15 mm, or between 1 mm and 4 mm. In some non-limiting examples, the width of the first fence wall 177, the width of the second fence wall 178, or the width of the third fence wall 179 may be between 0.5 and 15 mm, or between 1 mm and 4 mm.

[0060] In one non-limiting example, the set of dilution holes 160 may extend axially along a portion of the burner bushing 140, for example, to the midpoint or middle length of the burner bushing 140. In other examples, the set of dilution holes 160 may be arranged or spaced apart along the entire axial range of the burner bushing 140.

[0061] Furthermore, in the illustrated example, the second orifice 162 may include a set of discrete orifices 160S arranged circumferentially around the burner bushing 140. This set of discrete orifices 160S may include a plurality of discrete circumferentially extending slots extending at least partially around the burner bushing 140. The second fence wall 172 may also include a set of discrete walls 170S arranged circumferentially around the burner bushing 140. This set of discrete walls 170S may include a plurality of discrete walls positioned downstream of the plurality of discrete slots that collectively form the second orifice 162. Any combination of a single orifice, a plurality of discrete orifices, partially or fully annular circumferential slots, and optional downstream walls or fences may be provided.

[0062] Now for reference Figure 7 This shows that combustion can occur in section 14 ( Figure 1 This is a part of another burner 230 used in the burner. Burner 230 is similar to burners 30 and 130; therefore, similar parts will be described with similar numbers further increased by 100. It should be understood that, unless otherwise stated, the description of similar parts of burners 30 and 130 applies to burner 230.

[0063] The burner 230 may include a burner bushing 240, a dome assembly 244, a combustion chamber 250, and a set of dilution orifices 260. The set of dilution orifices 260 may include any number of dilution holes, openings, orifices, etc. These dilution orifices may be located on any part of the burner bushing 240. Figure 5 In the example, the set of dilution orifices 260 is schematically shown as having rectangular openings, and it should be understood that the set of dilution orifices 260 may have any suitable orifice profile, size, pattern, arrangement or number on the burner bushing 240, including linear rows, irregular groups, annular arrangements around the burner bushing 240, variable orifice diameters, constant orifice diameters, etc., or combinations thereof.

[0064] The set of dilution orifices 260 may include a first orifice 261, a second orifice 262, and a third orifice 263. One difference from burners 30 and 130 is that the first orifice 261 may include a row of discrete dilution orifices positioned annularly around burner bushing 240. The first orifice 261 may be positioned immediately adjacent to dome assembly 244. In the non-limiting example shown, the second orifice 262 and the third orifice 263 may each include a groove extending annularly around burner bushing 140. It is also envisioned that the amount of air entering combustion chamber 250 may vary across this set of dilution orifices 260.

[0065] A set of protruding walls or fences may also be provided in burner 230. Another difference from burners 30 and 130 is that the first orifice 261 does not include protruding walls or fences, formerly referred to as a first fence wall with a first height. A second fence wall 272 may be located downstream of the second orifice 262, and a third fence wall 273 may be located downstream of the third orifice 263. In some examples, the second fence wall 272 or the third fence wall 273 may comprise a continuous wall extending annularly around burner 230, or comprise multiple discrete or separate segments that collectively form a wall.

[0066] The second fence wall 272 and the third fence wall 273 may define corresponding second heights 282 and third heights 283. The second height 282 may be equal to, greater than, or less than the third height 283. Furthermore, either or both of the second fence wall 272 or the third fence wall 273 may have variable heights, including in the circumferential direction around the burner 230. In the non-limiting example shown, the second fence wall 272 defines a second height 282 in the first portion of the burner 230 and a fifth height 285 in the second portion of the burner 230. Furthermore, in the non-limiting example shown, the third fence wall 273 defines a third height 283 in the first portion of the burner 230 and a sixth height 286 in the second portion of the burner 230.

[0067] The second, third, fifth, and sixth heights 282, 283, 285, and 286 can also be formed in corresponding proportions. In some non-limiting examples: the ratio of the second height 282 to the fifth height 285 can be 0.1-5; the ratio of the third height 283 to the sixth height 286 can be 0.1-5; the ratio of the third height 283 to the second height 282 can be 0-15; or the ratio of the fifth height 285 to the sixth height 286 can be 0-1.5.

[0068] Some exemplary combustion flows C are also shown within the combustion chamber 250. A first jet J1 enters the combustion chamber 250 through a first orifice 261, a second jet J2 enters through a second orifice 262, and a third jet J3 enters through a third orifice 263. During operation, the first orifice 261 can be configured to guide the first jet J1 such that the combustion flow C or combustion flame is located away from the burner bushing 140 in the region near the dome assembly 244. The second orifice 262 and the second grid wall 272 can be configured to guide the second jet J2 to the center of the combustion chamber 150 and reduce or at least partially extinguish the flame in the core of the burner 230 with lower turbulence. The third orifice 263 and the third grid wall 273 can be configured to guide the third jet J3 into the combustion chamber 250, reduce the core temperature, and form or shape a desired exit profile and mode factor for the combustion gas flow exiting the burner 230. In this way, the heights of the grid walls 272 and 273 can be selected or adjusted to change or shape the location of the peak outlet temperature distribution within the burner 230. In an example where the third height 283 is smaller than the fifth height 285, the peak outlet temperature location can be shaped to be closer to the side of the combustion chamber 250 due to the asymmetric jet direction.

[0069] In some non-limiting examples where the second height 282 differs from the fifth height 285 or the third height 283 differs from the sixth height 286, a desired outlet temperature distribution of the combustion gases exiting the combustion chamber 250 can be formed due to asymmetric jet penetration.

[0070] Figure 8 A schematic top view of a portion of a burner bushing 240 is shown, which has the set of dilution orifices 260 (including a first orifice 261, a second orifice 262, and a third orifice 263) and a second grid wall 272 and a third grid wall 273.

[0071] In a non-limiting example, the set of dilution orifices 260 may extend axially along a portion of the burner bushing 240, including extending to the midpoint or intermediate length of the burner bushing 240. In other examples, the set of dilution orifices 260 may be arranged or spaced apart along the entire axial range of the burner bushing 240.

[0072] In the non-limiting example shown, the first orifice 261 may include the row of discrete dilution orifices, as described above. Figure 6As described herein. In some examples, the first orifice 261 may include a dilution orifice extending annularly around the burner bushing 240 in the circumferential direction, or extending partially around the burner bushing 240 in the circumferential direction, or may include multiple sets of dilution orifices. The second orifice 262 and the third orifice 263 may include elongated slots extending at least partially around the burner bushing 240 in the circumferential direction. As shown, the second fence wall 272 and the third fence wall 273 may be positioned downstream of the respective second orifice 262 and third orifice 263.

[0073] Another difference compared to burners 30 and 130 is that the second orifice 262 may have a non-constant second orifice width 268 along the burner bushing 240. In the non-limiting example shown, the second orifice width 268 may form a variable slot width at least in the circumferential direction around the burner bushing 240. In another non-limiting example, the second orifice width 268 may include a slot width having a narrower portion circumferentially adjacent to the wider portion, such that the slot width alternates between wide and narrow along different circumferential portions of the burner bushing 240.

[0074] Further aspects of this disclosure will now be described through some additional exemplary embodiments. It should be understood that such examples are provided for illustrative purposes and do not limit this disclosure in any way.

[0075] In one example, the set of dilution orifices may include a first row and a second row of discrete dilution orifices, each row extending circumferentially around the burner bushing in an annular pattern. The first row may be positioned immediately adjacent to the dome assembly, and the second row may be positioned downstream of the first row. In some examples, the first row may include dilution orifices larger than the second row. In some examples, the first and second rows may have dilution orifices of the same size. An annular groove may be positioned downstream of both rows. A protruding grid may be positioned directly downstream of the annular groove. In this way, the burner bushing can provide two rows of discrete dilution jets and a groove providing a third dilution jet, wherein the third dilution jet is directed toward the center of the combustion chamber and configured to shape the combustion gas flow through the protruding grid.

[0076] In another example, the set of dilution orifices may include a single row of discrete dilution orifices positioned adjacent to the dome assembly and a single annular groove downstream of the row of discrete dilution orifices. A fence may be provided downstream of the annular groove. In this way, the burner bushing can provide a row of discrete dilution jets and a dilution jet provided by the groove, the dilution jet provided by the groove being configured to shape the combustion gas flow through the fence.

[0077] In another example, the set of dilution orifices may include a row of discrete dilution orifices positioned adjacent to the dome assembly, and a plurality of slots positioned downstream of that row. In some examples, the plurality of slots may include an annular slot that together forms a ring extending around the burner bushing and a plurality of discrete slots. In some examples, a fence may be positioned downstream of each of the annular slot and the plurality of discrete slots. In some examples, a plurality of discrete fences may be positioned downstream of each of the plurality of discrete slots. In some examples, the discrete slots may be arranged on multiple rows and circumferentially staggered with each other. Corresponding circumferentially staggered fences may also be positioned downstream of the circumferentially staggered slots.

[0078] In another example, the set of dilution orifices may include an annular groove extending around the burner bushing, without a barrier. In this case, the jet entering the burner can remain close to the burner bushing, providing cooling to the bushing and shaping the flame away from the bushing.

[0079] The aspects described in this disclosure offer several benefits, including that the set of dilution orifices or protruding walls / barriers can provide a more uniform temperature distribution downstream of the dilution jet. This improved temperature distribution can also reduce unwanted emissions, including NO. x This set of dilution orifices and grilles can also provide the location for modifying or customizing the peak burner outlet temperature distribution or pattern. The grilles described herein offer several benefits, including higher grilles providing flame extinguishing or flow mixing within the combustion chamber, and shorter grilles providing cooling for the burner bushings. This set of dilution orifices or protruding walls can provide reduced ambient temperatures on the deflector and bushings, which can extend component life.

[0080] Furthermore, using a higher volume jet near the dome assembly can extinguish the temperature within the burner core and control, for example, the maximum heat release zone between the first and second jets. Using a lower volume jet (e.g., a third jet) at the rear of the burner bushing can provide lower temperatures near the bushing at the burner's rear end. Using a lower volume jet can help shape the flame away from the grid, while using a higher volume jet can help extinguish the flame to achieve a more uniform temperature distribution.

[0081] The various custom jets described in this article can provide the ability to shape or customize the outlet temperature distribution to a desired distribution, which also provides increased component life. The use of annular groove flow can form a well-defined film on the grid, outer liner, and inner liner, which can provide a circumferentially uniform flow distribution, thereby improving uniform heat release control around the entire burner liner perimeter.

[0082] 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.

[0083] Further aspects of this disclosure are provided in the following terms:

[0084] A turbine engine includes: a compressor section, a combustion section, and a turbine section arranged in a series flow configuration, wherein the combustion section has a combustor defining a combustor axis and includes: a combustor bushing at least partially defining a combustion chamber; a dome assembly coupled to the combustor bushing and at least partially defining the combustion chamber; a compressed air passage fluidly connecting the compressor section to the combustion chamber; a first orifice extending adjacent to the dome assembly through the combustor bushing and fluidly connecting the compressed air passage to the combustion chamber; a second orifice extending through the combustor bushing and axially spaced downstream of the first orifice along the combustor axis; and a fence wall located downstream of the second orifice and projecting radially from the combustor bushing into the combustion chamber relative to the combustor axis.

[0085] The turbine engine according to any of the foregoing clauses further includes a plurality of orifices arranged circumferentially about the burner bushing relative to the burner axis, wherein the plurality of orifices includes at least one of the first orifice or the second orifice.

[0086] The turbine engine according to any of the foregoing clauses, wherein at least one of the first orifice or the second orifice includes a circumferentially extending groove.

[0087] The turbine engine according to any of the foregoing clauses, wherein the burner defines a burner length and the first orifice defines a first orifice distance, wherein the burner length and the first orifice distance are defined relative to the dome assembly along the burner axis, wherein the first orifice distance is between 0.01 and 0.2 times the burner length.

[0088] The turbine engine according to any of the foregoing clauses, wherein the second orifice includes the circumferentially extending groove and has a variable orifice width.

[0089] The turbine engine according to any of the foregoing clauses further includes an additional grid wall that projects radially from the combustor bushing into the combustion chamber.

[0090] According to any of the preceding clauses, the additional grid wall and the grid wall have different axial positions relative to the combustor axis.

[0091] The turbine engine according to any of the foregoing clauses, wherein the additional fence wall is positioned upstream of the fence wall and downstream of the first orifice.

[0092] The turbine engine according to any of the foregoing clauses, wherein the additional fence wall includes a first height, and the fence wall includes a second height greater than the first height.

[0093] The turbine engine according to any of the foregoing clauses, wherein at least one of the grid wall or the additional grid wall comprises a plurality of discrete walls arranged circumferentially around the burner bushing relative to the burner axis.

[0094] According to any of the preceding clauses, the turbine engine, wherein the fence wall defines a second length from the additional fence wall, and wherein the second length is between 0.1 and 0.6 times the length of the burner.

[0095] The turbine engine according to any of the foregoing clauses, wherein the grid wall comprises a continuous grid wall that extends circumferentially about the burner bushing relative to the burner axis.

[0096] The turbine engine according to any of the foregoing clauses further includes a third orifice downstream of the second orifice and a third grid wall that radially protrudes into the combustion chamber downstream of the third orifice.

[0097] According to any of the preceding clauses, the turbine engine, wherein the second orifice comprises a set of discrete orifices arranged circumferentially, and wherein the fence wall comprises a set of discrete walls arranged circumferentially, wherein each of the set of discrete walls is positioned downstream of each corresponding discrete orifice in the set of discrete orifices.

[0098] The turbine engine according to any of the foregoing clauses further includes a third orifice, a first grid wall, a second grid wall, and a third grid wall extending through the burner bushing.

[0099] The turbine engine according to any of the foregoing clauses, wherein the second fence wall is the fence wall.

[0100] The turbine engine according to any of the foregoing clauses, wherein the first fence wall is the additional fence wall.

[0101] The turbine engine according to any of the foregoing clauses, wherein the first fence wall includes a first height and a fourth height, the second fence wall includes a second height and a fifth height, and the third fence wall includes a third height and a sixth height.

[0102] The turbine engine according to any of the foregoing clauses, wherein the ratio of the first height to the fourth height is between 0.1 and 5.

[0103] The turbine engine according to any of the foregoing clauses, wherein the ratio of the second height to the fifth height is between 0.1 and 5.

[0104] The turbine engine according to any of the foregoing clauses, wherein the ratio of the third height to the sixth height is between 0.1 and 5.

[0105] The turbine engine according to any of the foregoing clauses, wherein the ratio of the first height to the dome height is between 0.005 and 0.2.

[0106] According to any of the foregoing clauses, the ratio of the second height to the first height is between 0 and 15.

[0107] The turbine engine according to any of the foregoing clauses, wherein the ratio of the fifth height to the fourth height is between 0 and 15.

[0108] According to any of the foregoing clauses, the ratio of the third height to the first height is between 0 and 15.

[0109] According to any of the foregoing clauses, the ratio of the sixth height to the first height is between 0 and 15.

[0110] The turbine engine according to any of the foregoing clauses further includes a third orifice extending through the burner bushing and a third fence wall downstream of the third orifice.

[0111] The turbine engine according to any of the foregoing clauses, wherein the fence wall includes a second height and a fifth height, and wherein the third fence wall includes a third height and a sixth height.

[0112] The turbine engine according to any of the foregoing clauses, wherein the ratio of the second height to the fifth height is between 0.1 and 5.

[0113] The turbine engine according to any of the foregoing clauses, wherein the ratio of the third height to the sixth height is between 0.1 and 5.

[0114] According to any of the foregoing clauses, the ratio of the third height to the second height is 0-15.

[0115] The turbine engine according to any of the foregoing clauses, wherein the ratio of the fifth height to the sixth height is 0-1.5.

[0116] The turbine engine according to any of the foregoing clauses further includes a first jet through the first orifice, a second jet through the second orifice, and a third jet through the third orifice.

[0117] The turbine engine according to any of the foregoing clauses, wherein the first jet is larger than the second jet.

[0118] According to any of the foregoing clauses, the turbine engine wherein the first jet is larger than the third jet.

[0119] According to any of the preceding clauses, the turbine engine wherein the first jet comprises 1-20% of the total dilution flow through the set of dilution orifices.

[0120] According to any of the foregoing clauses, the third jet comprises 0-40% of the total dilution flow through the set of dilution orifices.

[0121] According to any of the foregoing clauses of the turbine engine, the second jet comprises 80-100% of the total dilution flow through the set of dilution orifices.

[0122] A combustor for a turbine engine includes: a combustor bushing that at least partially defines a combustion chamber along a combustor axis; a dome assembly coupled to the combustor bushing and at least partially defining the combustion chamber; a compressed air passage that fluidly connects the combustion chamber to a compressed air source; a first orifice extending adjacent to the dome assembly through the combustor bushing and fluidly connecting the compressed air passage to the combustion chamber; a second orifice extending through the combustor bushing and axially spaced downstream of the first orifice along the combustor axis; and a fence wall located downstream of the second orifice and projecting radially from the combustor bushing into the combustion chamber relative to the combustor axis.

[0123] The burner according to any of the foregoing clauses further includes a plurality of orifices arranged circumferentially around the burner bushing relative to the burner axis, wherein the plurality of orifices includes at least one of the first orifice or the second orifice.

[0124] The burner according to any of the foregoing clauses, wherein the burner defines a burner length and the first orifice defines a first orifice distance, wherein the burner length and the first orifice distance are defined relative to the dome assembly along the burner axis, wherein the first orifice distance is between 0.01 and 0.2 times the burner length.

[0125] According to any of the preceding clauses, in a burner, at least one of the first orifice or the second orifice includes a circumferentially extending groove having a variable orifice width.

[0126] The burner according to any of the foregoing clauses further includes an additional grid wall that projects radially from the burner bushing into the combustion chamber.

[0127] According to any of the preceding clauses, the burner is wherein the additional grid wall is positioned upstream of the grid wall and downstream of the first orifice.

[0128] According to any of the preceding clauses, the additional grid wall includes a first height, and the grid wall includes a second height greater than the first height.

[0129] According to any of the preceding clauses, the burner comprises at least one of the grid wall or the additional grid wall, which includes a plurality of discrete walls arranged circumferentially around the burner bushing relative to the burner axis.

[0130] The burner according to any of the foregoing clauses, wherein the burner defines a burner length relative to the dome assembly, and the additional grid wall defines a first length from the dome assembly, wherein the first length is between 0.01 and 0.2 times the burner length.

[0131] According to any of the preceding clauses, the burner is wherein the grid wall defines a second length from the additional grid wall, and wherein the second length is between 0.1 and 0.6 times the length of the burner.

[0132] According to any of the preceding clauses, the burner includes a continuous grid wall that extends circumferentially about the burner bushing relative to the burner axis.

[0133] The burner according to any of the foregoing clauses further includes a third orifice, a first grid wall, a second grid wall, and a third grid wall extending through the burner bushing.

[0134] The burner according to any of the foregoing clauses, wherein the second grid wall is the grid wall.

[0135] The burner according to any of the foregoing clauses, wherein the first grid wall is the additional grid wall.

[0136] According to any of the preceding clauses, the burner includes a first height and a fourth height, the second fence wall includes a second height and a fifth height, and the third fence wall includes a third height and a sixth height.

[0137] According to any of the foregoing clauses, the ratio of the first height to the fourth height is between 0.1 and 5.

[0138] According to any of the foregoing clauses, the ratio of the second height to the fifth height is between 0.1 and 5.

[0139] According to any of the preceding clauses, the ratio of the third height to the sixth height is between 0.1 and 5.

[0140] According to any of the foregoing clauses, the ratio of the first height to the dome height is between 0.005 and 0.2.

[0141] According to any of the foregoing clauses, the ratio of the second height to the first height is between 0 and 15.

[0142] According to any of the preceding clauses, the ratio of the fifth height to the fourth height is between 0 and 15.

[0143] According to any of the foregoing clauses, the ratio of the third height to the first height is between 0 and 15.

[0144] According to any of the preceding clauses, the ratio of the sixth height to the first height is between 0 and 15.

[0145] The burner according to any of the foregoing clauses further includes a third orifice extending through the burner bushing and a third fence wall downstream of the third orifice.

[0146] The burner according to any of the foregoing clauses, wherein the grid wall includes a second height and a fifth height, and wherein the third grid wall includes a third height and a sixth height.

[0147] According to any of the foregoing clauses, the ratio of the second height to the fifth height is between 0.1 and 5.

[0148] According to any of the preceding clauses, the ratio of the third height to the sixth height is between 0.1 and 5.

[0149] According to any of the foregoing clauses, the ratio of the third height to the second height is 0-15.

[0150] According to any of the preceding clauses, the ratio of the fifth height to the sixth height is 0-1.5.

[0151] The burner according to any of the foregoing clauses further includes a first jet through the first orifice, a second jet through the second orifice, and a third jet through the third orifice.

[0152] According to any of the foregoing clauses, the first jet is greater than the second jet.

[0153] According to any of the preceding clauses, the burner wherein the first jet is greater than the third jet.

[0154] According to any of the preceding clauses, the burner wherein the first jet comprises 1-20% of the total dilution flow through the set of dilution orifices.

[0155] According to any of the preceding clauses, the burner wherein the third jet comprises 0-40% of the total dilution flow through the set of dilution orifices.

[0156] According to any of the preceding clauses, the burner wherein the second jet comprises 80-100% of the total dilution flow through the set of dilution orifices.

Claims

1. A turbine engine, characterized in that, include: A compressor section, a combustion section, and a turbine section are arranged in a series flow configuration, wherein the combustion section has a burner that defines a burner axis and includes: A burner bushing, the burner bushing at least partially comprising a combustion chamber, the burner bushing defining an outer liner and an inner liner; A dome assembly, which is coupled to the burner bushing and at least partially defines the combustion chamber; A compressed air passage that fluidly connects the compressor section to the combustion chamber; A first orifice extends adjacent to the dome assembly through the burner bushing and fluidly connects the compressed air passage to the combustion chamber; A second orifice extends through the burner bushing and is axially spaced downstream of the first orifice along the burner axis; A fencing wall, located downstream of the second orifice, and projecting radially from the outer liner into the combustion chamber relative to the burner axis; and An additional grid wall is located downstream of the second orifice and projects radially from the liner into the combustion chamber relative to the burner axis; the grid wall and the additional grid wall are axially aligned along the burner axis. Each of the fence wall and the additional fence wall is configured to guide fluid flow from at least one of the first orifice or the second orifice to the center of the burner, so as to move the combustion flame away from the burner bushing.

2. The turbine engine according to claim 1, characterized in that, It further includes a plurality of orifices arranged circumferentially around the burner bushing relative to the burner axis, wherein the plurality of orifices includes at least one of the first orifice or the second orifice.

3. The turbine engine according to claim 1, characterized in that, in, At least one of the first orifice or the second orifice includes a circumferentially extending groove.

4. The turbine engine according to claim 1, characterized in that, in, The burner defines a burner length and the first orifice defines a first orifice distance, wherein the burner length and the first orifice distance are defined relative to the dome assembly along the burner axis, and wherein the first orifice distance is between 0.01 and 0.2 times the burner length.

5. The turbine engine according to claim 1, characterized in that, in, The additional fence wall includes a first height, and the fence wall includes a second height greater than the first height.

6. The turbine engine according to claim 1, characterized in that, in, At least one of the fence wall or the additional fence wall includes a plurality of discrete walls arranged circumferentially around the burner bushing relative to the burner axis.

7. The turbine engine according to claim 1, characterized in that, in, The fence wall includes a continuous fence wall that extends circumferentially around the burner bushing relative to the burner axis.

8. The turbine engine according to claim 1, characterized in that, It further includes a third orifice downstream of the second orifice and a third grid wall that protrudes radially into the combustion chamber downstream of the third orifice.

9. The turbine engine according to claim 8, characterized in that, in, The second orifice includes a set of discrete orifices arranged circumferentially, and the fence wall includes a set of discrete walls arranged circumferentially, wherein each of the discrete walls is positioned downstream of each corresponding discrete orifice in the set of discrete orifices.

10. A combustor for a turbine engine, characterized in that, include: A burner bushing that at least partially defines a combustion chamber along a burner axis, the burner bushing comprising an outer liner and an inner liner; A dome assembly, which is coupled to the burner bushing and at least partially defines the combustion chamber; A compressed air passage that fluidly connects the combustion chamber to a compressed air source; A first orifice extends adjacent to the dome assembly through the burner bushing and fluidly connects the compressed air passage to the combustion chamber; A second orifice extends through the burner bushing and is axially spaced downstream of the first orifice along the burner axis; A first fence wall, located downstream of the second orifice, and projecting radially from the outer liner into the combustion chamber relative to the burner axis; as well as The second grid wall is located downstream of the second orifice and projects radially from the liner into the combustion chamber relative to the burner axis; The first and second grid walls are axially aligned along the burner axis, and each of the first and second grid walls is configured to guide fluid flow from at least one of the first orifice or the second orifice to the center of the burner, thereby distancing the combustion flame away from the burner bushing.

11. The burner according to claim 10, characterized in that, It further includes a plurality of orifices arranged circumferentially around the burner bushing relative to the burner axis, wherein the plurality of orifices includes at least one of the first orifice or the second orifice.

12. The burner according to claim 10, characterized in that, in, The burner defines a burner length and the first orifice defines a first orifice distance, wherein the burner length and the first orifice distance are defined relative to the dome assembly along the burner axis, and wherein the first orifice distance is between 0.01 and 0.2 times the burner length.

13. The burner according to any one of claims 10-12, characterized in that, It further includes an additional grid wall that projects radially from the burner bushing into the combustion chamber.

14. The burner according to claim 13, characterized in that, in, The additional fence wall is positioned upstream of the first fence wall and downstream of the first opening.

15. The burner according to claim 13, characterized in that, in, The additional fence wall includes a first height, and the first fence wall includes a second height greater than the first height.

16. The burner according to claim 13, characterized in that, in, At least one of the first fence wall or the additional fence wall includes a plurality of discrete walls arranged circumferentially around the burner bushing relative to the burner axis.

17. The burner according to claim 10, characterized in that, in, The first fence wall includes a continuous fence wall that extends circumferentially around the burner bushing relative to the burner axis.

Images