Gas turbine engine combustor with a set of dilution passages

Abstract

A combustor includes a dome wall, an annular liner, a combustion chamber, a set of fuel cups, and a set of dilution passages for each fuel cup in the set of fuel cups. The set of fuel cups are spaced circumferentially along the dome wall relative to a combustor centerline. The set of dilution passages terminate at a plurality of slots spaced around a corresponding fuel cup in the set of fuel cups.

Description

Technical Field

[0001] This topic generally relates to gas turbine engine combustors having a set of dilution channels, and more specifically, to combustors having a set of dilution channels located in the dome wall. Background Technology

[0002] A gas turbine engine is driven by a flow of combustion gases through the engine to rotate multiple turbine blades. A combustor may be located within the gas turbine engine and fluidly connected to the turbine through which the combustion gases flow.

[0003] Hydrocarbon fuels are commonly used in the combustors of gas turbine engines. Typically, air and fuel are fed separately into the combustor until they mix and the mixture burns to produce hot combustion gases. These combustion gases are then fed into the turbine, where they rotate to generate power. Byproducts of hydrocarbon fuel combustion typically include nitrogen oxides and nitrogen dioxide (collectively known as NO). x Carbon monoxide (CO), unburned hydrocarbons (UHC) (e.g., methane and volatile organic compounds that contribute to the formation of atmospheric ozone), and other oxides including oxides of sulfur (e.g., SO2 and SO3). Attached Figure Description

[0004] In the attached image:

[0005] Figure 1 This is a schematic diagram of a gas turbine engine.

[0006] Figure 2 Depicting along Figure 1 A cross-sectional view of the combustion section of the gas turbine engine in line II-II.

[0007] Figure 3 It is based on the aspects disclosed in this article. Figure 2 A schematic diagram of a side cross-sectional view of the burner in the combustion zone formed by a burner bushing with multiple sets of dilution channels, taken from line III-III.

[0008] Figure 4 It is set to apply Figure 3 A schematic cross-sectional view of the arrangement of the first dilution channels on the dome wall inside the burner.

[0009] Figure 5 From Figure 4 The line V seen Figure 4 A partial side cross-sectional view of a portion of the first dilution channel arrangement, showing the first channel angle defining the first orientation of the dilution channels.

[0010] Figure 6 From Figure 4Line VI shows a partial side cross-sectional view of a portion of the first dilution channel arrangement, illustrating the first channel angle that defines the second orientation of the dilution channels.

[0011] Figure 7 From Figure 4 Line VII Figure 4 A partial side cross-sectional view of a portion of the first dilution channel arrangement, showing the first channel angle defining the third orientation of the dilution channels.

[0012] Figure 8 From Figure 4 The enlarged schematic front view of the dome wall seen in section VIII, with the dilution channel including the second channel angle.

[0013] Figure 9 It includes Figure 4 A schematic front view of the dome wall of the dilution channel arrangement further illustrates the flame forming attributable to the dilution channels.

[0014] Figure 10 It is suitable for use as Figure 4 A schematic transverse view of a second dilution channel arrangement, which includes multiple slots following a spiral pattern.

[0015] Figure 11 It is suitable for use as Figure 4 A schematic transverse view of a third dilution channel arrangement, which includes a first subgroup of slots following a curve and a second subgroup of slots following a linear line.

[0016] Figure 12 It is suitable for use as Figure 4 A schematic transverse view of a fourth dilution channel arrangement, which includes a first subgroup of slots following a curve and a second subgroup of slots following a linear line extending non-circumferentially around the dome wall.

[0017] Figure 13 It is suitable for use as Figure 4 A schematic transverse view of the fifth dilution channel arrangement, which includes multiple slots following non-circular polygonal paths.

[0018] Figure 14 It is suitable for use as Figure 4 A schematic transverse view of the sixth dilution channel arrangement, which includes multiple slots with asymmetrical formation.

[0019] Figure 15 It is suitable for use as Figure 4 A schematic transverse view of the seventh dilution channel arrangement, which includes multiple channels with different cross-sectional areas.

[0020] Figure 16 It is suitable for use as Figure 4 A schematic transverse view of an eighth dilution channel arrangement, which includes multiple channels having a first row of channels and a second row of channels. Detailed Implementation

[0021] The disclosed aspects described herein relate to a burner. The burner includes a combustion chamber at least partially defined by a dome wall. A set of fuel cups is arranged annularly on the dome wall and fluidly connected to the combustion chamber. A dilution channel arrangement is provided around each fuel cup in the set. The dilution channel arrangement of each fuel cup can be selected to work with adjacent fuel cups, and their corresponding dilution channels are arranged to jointly control the annular flame spread from all fuel cups, and individually control the flame spread from each fuel cup. Each dilution channel arrangement includes a set of dilution channels terminating in a plurality of slots arranged along the dome wall. As described herein, a single “dilution channel arrangement” refers to a plurality of slots arranged around a single corresponding fuel cup in the set. It should be understood that any number of dilution channel arrangements is possible. For example, the total number of dilution channel arrangements may correspond to the total number of fuel cups in the set.

[0022] For illustrative purposes, this disclosure will be described in relation to gas turbine engines. However, it will be understood that the aspects of the disclosure described herein are not limited thereto, and the combustor described herein can be implemented in engines (including, but not limited to, turbojet engines, turboprop engines, turboshaft engines, and turbofan engines). The aspects of the disclosure discussed herein are generally applicable to non-aircraft engines with combustors, such as in other mobile applications and non-mobile industrial, commercial, and residential applications.

[0023] The term "exemplary" as used herein means "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as superior to or advantageous to other implementations. Furthermore, unless explicitly stated otherwise, all embodiments described herein should be considered exemplary.

[0024] 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.

[0025] 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.

[0026] As used herein, the term "upstream" refers to the direction opposite to the direction of fluid flow, while the term "downstream" refers to the direction in the same direction as the fluid flow. The terms "forward" or "front" indicate what is in front of something, and "backward" or "rear" indicate what is behind something. For example, when used in relation to fluid flow, forward / front can indicate upstream, and backward / rear can indicate downstream.

[0027] 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.

[0028] Furthermore, as used herein, the term "radial" or "radially" refers to a direction away from a common center. For example, in the overall context of a gas turbine engine, radial refers to the direction along a ray extending between the engine's central longitudinal axis and the engine's outer perimeter.

[0029] 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 for identification purposes only to aid the reader in understanding this disclosure and do not impose limitations, particularly regarding the location, orientation, or use of the 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.

[0030] 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.

[0031] 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.

[0032] Figure 1 This is a schematic diagram of a gas turbine engine 10. As a non-limiting example, the gas turbine engine 10 can be used within an aircraft. The gas turbine engine 10 may include at least a compressor section 12, a combustion section 14, and a turbine section 16 arranged in series for flow. 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 axis of rotation or engine centerline 21 of the gas turbine engine 10.

[0033] Compressor section 12 may include a low-pressure (LP) compressor 22 and a high-pressure (HP) compressor 24 fluidly connected in series with each other. Turbine section 16 may include an LP turbine 26 and an HP turbine 28 fluidly connected in series with each other. Drive shaft 18 may operatively connect the LP compressor 22, HP compressor 24, LP turbine 26, and HP 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 26, and the HP drive shaft may connect the HP compressor 24 to the HP turbine 28. The LP spool may be defined as a combination of the LP compressor 22, LP turbine 26, and LP drive shaft, such that rotation of the LP turbine 26 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 28, and HP drive shaft, such that rotation of the HP turbine 28 may apply a driving force to the HP drive shaft, which in turn may rotate the HP compressor 24.

[0034] 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. The 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 gas turbine engine 10. It should be understood that the representation of compressor section 12 is merely illustrative and any number of stages may be present. Furthermore, it is contemplated that any other number of components may be present within compressor section 12.

[0035] 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 other number of components may be present within turbine section 16.

[0036] 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 28 at its downstream end.

[0037] During operation of the gas 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 28 extracts some work from these combustion gases, driving the HP compressor 24. The combustion gases are discharged into the LP turbine 26, which extracts additional work to drive the LP compressor 22, and the exhaust gas is ultimately discharged from the gas turbine engine 10 via an exhaust section (not shown) downstream of the turbine section 16. The drive of the LP turbine 26 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 gas turbine engine 10.

[0038] Figure 2 Depicting along Figure 1 A cross-sectional view of combustion section 14 along line II-II. Combustion section 14 may include a set of fuel cups 76 arranged around burner centerline 36. Burner centerline 29 may be centerline 21 of turbine engine 10. Burner centerline 36 may be the centerline of combustion section 14, a single burner, or a set of burners arranged around burner centerline 36.

[0039] Depending on the type of engine in which the burner 80 is located, the burner 80 may have a canister-shaped, canister-annular, or annular arrangement. In a non-limiting example, an annular arrangement is shown and disposed within the housing 78. The burner 80 is defined by a burner bushing 82, which includes an outer annular burner bushing 82a and an inner annular burner bushing 82b that are concentric with each other and annular about the burner centerline 36. A dome assembly 84 including a dome wall 90, together with the burner bushing 82, may define a combustion chamber 86 annular about the burner centerline 36. At least one fuel cup 76 (shown as a plurality of fuel injectors arranged annularly about the burner centerline 36) is fluidly coupled to the combustion chamber 86. A compressed air passage 88 may be defined at least partially by the burner bushing 82 and the housing 78.

[0040] At least one fuel cup 76 is included within a plurality of fuel cups 76. Each fuel cup 76 may include a fuel cup center line 34 extending into the page. Each fuel cup center line 34 may be arranged along a circumferential line 70. Alternatively, one or more fuel cups 76 may be offset from the circumferential line 70. Furthermore, the fuel cups 76 may be arranged such that the fuel cup center line 34 is relative to the circumferential line 70 but does not necessarily form a pattern on the circumferential line 70.

[0041] Each fuel cup centerline 34, in conjunction with the burner centerline 36, can be used to define a corresponding fuel cup reference line 30 extending radially from the burner centerline 36 and passing through the corresponding fuel cup centerline 34. For illustrative purposes, four fuel cup reference lines 30 are shown; however, it should be understood that each fuel cup 76 includes a fuel cup reference line 30. The fuel cup reference lines 30 are used in this specification to establish a local polar coordinate system 32 for each fuel cup 76. The local polar coordinate system defines a 0-180 degree line on the corresponding reference line 30, and a 90-270 degree line for each of the four shown fuel cup reference lines 30. For convenience, the 0-degree and 90-degree lines are shown on each polar coordinate system 32. Since the fuel cups 76 are circumferentially spaced around the burner centerline 36, a polar coordinate system based on the fuel cup reference lines 30 is a convenient way to describe the local fuel cups 76, while taking into account rotational offsets due to circumferential arrangement in the local coordinate system.

[0042] Figure 3 Depicting along Figure 2 The cross-sectional view taken by line III-III shows the combustion section 14. The first set of dilution channels 92, the second set of dilution channels 93, and the third set of dilution channels 94 are fluidly connected to the compressed air passage 88 and the burner 80.

[0043] Fuel cup 76 can be coupled to and disposed within dome assembly 84. Fuel cup 76 may include a flared cone 104 and a swirler 112. Flared cone 104 includes an outlet 96 of fuel cup 76 that is directly fluidly coupled to combustion chamber 86. Fuel cup 76 is fluidly coupled to fuel inlet 98 via linear passage 100.

[0044] Both the inner burner liner 82a and the outer burner liner 82b can have an outer surface 106 and an inner surface 108 that at least partially define the combustion chamber 86. The burner liner 82 can be made from a single continuous integral part or can be multiple integral parts assembled together to define the inner burner liner 82a and the outer burner liner 82b. As a non-limiting example, the outer surface 106 can define a first piece of the burner liner 82, while the inner surface 108 can define a second piece of the burner liner 82, which, when assembled together, form the burner liner 82. As described herein, the burner liner 82 includes a third set of dilution channels 94. It is also contemplated that the burner liner 82 can be any type of burner liner 82, including but not limited to single-wall or double-wall liners or tile liners. The igniter 110 can be disposed at the burner liner 82 and fluidly coupled to the combustion chamber 86 at any location (as a non-limiting example, upstream of the third set of dilution channels 94).

[0045] During operation, compressed air (C) flows from compressor section 12 to burner 80 via dome assembly 84. The compressed air (C) is supplied to fuel cup 76 as a swirling airflow (S) via swirler 112. Fuel flow (F) is supplied to fuel cup 76 via fuel inlet 98 and linear passage 100. The swirling airflow (S) and fuel flow (F) mix at flared cone 104 and are supplied as a fuel / air mixture to combustion chamber 86. Ignition device 110 can ignite the fuel / air mixture to define a flame within combustion chamber 86, which generates combustion gases (G). Although shown axially downstream from outlet 96, it should be understood that the fuel / air mixture can be ignited at or near outlet 96.

[0046] Compressed air (C) is further supplied as a first dilution flow (D1) to dilution channels 92 and 93, and as a second dilution flow (D2) to a third set of dilution channels 94. The first dilution flow (D1) is used to guide and shape the flame, while the second dilution flow (D2) is used to guide the combustion gases (G).

[0047] Figure 3 The burner 80 shown is well-suited for using hydrogen-containing gas as fuel because it helps accommodate the faster-moving flame front associated with hydrogen fuel compared to conventional hydrocarbon fuels. However, the burner 80 can also be used with conventional hydrocarbon fuels.

[0048] Figure 4 Is it suitable for Figure 3 A schematic transverse cross-sectional view of the first dilution channel arrangement 200 on the dome wall 202 used within the burner 80. Therefore, the first dilution channel arrangement 200 and similar portions of the burner 80 will be given similar names, and it should be understood that, unless otherwise stated, the description of similar portions of the burner 80 applies to the first dilution channel arrangement 200. The first dilution channel arrangement 200 is disposed on the dome wall 202 around a fuel cup 204 having a fuel cup centerline 210 and an outlet 205. The dome wall 202 extends between an outer liner 206 and an inner liner 208.

[0049] Multiple dilution channels 212 extend through the dome wall 202 and include multiple slots 214. Each of the multiple slots 214 defines the termination point of one or more of the multiple dilution channels 212. Each dilution channel 212 extends along a channel centerline 234, which terminates at the corresponding slot 214 to define the center point of the corresponding slot 214 (indicated by the channel centerline 234 on each dilution channel in each slot 214). The multiple slots 214 are circumferentially spaced around at least a portion of the fuel cup centerline 210. As a non-limiting example, a single dilution channel 212 terminates in a single slot 214. However, a dilution channel may have multiple branches, each branch terminating in a slot. When viewed along a vertical plane perpendicular to the fuel cup centerline 210 and intersecting the slots 214, each of the multiple slots 214 is defined by a cross-sectional area. The cross-sectional area can be any suitable shape, such as, but not limited to, oblong, oval, elliptical, circular, elongated, rectangular, triangular, etc. Furthermore, the cross-sectional area can be uniform or non-uniform among the multiple slots 214, such that one or more slots can be larger than another slot or include different shapes.

[0050] At least a portion of the plurality of slots 214 is arranged such that the channel centerline 234 is aligned with the first line 216. Another portion of the plurality of slots 214 is arranged such that their channel centerlines 234 are aligned with the second line 218. As shown, the first line 216 and the second line 218 are arcs centered on the fuel cup centerline 210. Some of these additional paths are... Figure 10-16 The different arrangements shown are illustrated.

[0051] The first dilution channel arrangement 200 can be positioned relative to a polar coordinate system 269 around the fuel cup 204. The polar coordinate system 269 includes a line defining the fuel cup reference line 272 from 0 degrees to 180 degrees and a line defining the lateral reference line 270 from 90 degrees to 270 degrees. The polar coordinate system 269 can be divided into four quadrants: a first quadrant 274 between 0 and 90 degrees, a second quadrant 276 between 90 and 180 degrees, a third quadrant 278 between 180 and 270 degrees, and a fourth quadrant 280 between 270 and 360 degrees.

[0052] The first line 216 and the second line 218 each define an arc segment extending circumferentially around at least a portion of the fuel cup centerline 210. These arc segments are defined as arc segments with grooves. A first interruption 220 and a second interruption 222 are formed circumferentially between the first line 216 and the second line 218. The first interruption 220 and the second interruption 222 define opposing groove-free arc segments. The first interruption 220 is disposed within + / -75 degrees of the lateral reference line 270. The second interruption 222 is disposed within + / -75 degrees of the lateral reference line 270.

[0053] The first line 216 and the second line 218, and thus the plurality of slots 214, may extend across or within any suitable portion of the polar coordinate system 269. As a non-limiting example, the first line 216 or the second line 218, and thus the plurality of slots 214, may extend between at least two adjacent quadrants.

[0054] The first dilution channel arrangement 200 is symmetrical or asymmetrical about at least one of the transverse reference line 270 or the fuel cup reference line 272.

[0055] During operation, a fuel / air mixture (F1) is supplied through outlet 205 of fuel cup 204. The fuel / air mixture (F1) may exit fuel cup 204 in a straight line or otherwise include circumferential swirl, thereby defining the fuel / air mixture (F1) as a swirling fuel / air mixture. When swirling, the fuel / air mixture (F1) includes a circumferential component relative to the fuel cup centerline 210. A plurality of slots 214 surround at least a portion of the fuel / air mixture (F1).

[0056] Figure 5-7 Various non-limiting configurations of a plurality of dilution channels 212 extending through the dome wall 202 are shown. Each dilution channel 212 extends between an inlet 228 and a corresponding slot 214. The channel centerline 234 extends linearly or non-linearly. The fuel cup 204 includes a flared cone 230 having a flared surface 232 opening upward toward an outlet 205. The dome wall 202, outer liner 206, and inner liner 208 ( Figure 4 The combustion chamber 224 is at least partially defined. The outlet 205 of the fuel cup 204 and the slot 214 of the dilution passage 212 are each directly fluidly connected to a corresponding portion of the combustion chamber 224. It should be understood that the dilution passage 212 can take any suitable form and include any other suitable structure. As a non-limiting example, the inlet 228 may flare outward to define a funnel or otherwise include a sloping groove extending axially from the dome wall 202 relative to the passage centerline 234.

[0057] Figure 5 It shows from Figure 4 The image shows a partial cross-sectional side view of one of the multiple dilution channels 212 as seen from line V. The channel centerline 234 of the dilution channel 212 shown extends parallel to the fuel cup centerline 210, forming an axial dilution channel.

[0058] The channel centerline 234 (particularly its location at the slot 214 (e.g., the center point of the slot 214)) is positioned at a first radial height (Rhl) from the fuel cup centerline 210. The slot 214 is defined by a slot width (Sw). The dilution channel 212 extends from the inlet 228 to the slot 214 with a total axial length (La) relative to the fuel cup centerline 210. The outlet 205 of the fuel cup 204 extends a second radial height (Rh2) from the fuel cup centerline 210. As a non-limiting example, the outlet 205 is circular, such that the second radial height (Rh2) is the radius of the outlet 205, and twice the second radial height (Rh2) is the width of the outlet 205.

[0059] The ratio between the second radial height (Rh2) and the first radial height (Rhl) is greater than or equal to 1 and less than or equal to 3. The ratio between the slot width (Sw) and the width of the outlet 205 (e.g., twice the second radial height (Rh2)) is greater than or equal to 0.03 and less than or equal to 0.5. The slot width (Sw) can be any suitable size, such as greater than or equal to 0.04 inches. The ratio between the total axial length (La) and the slot width (Sw) can be greater than or equal to 0.1 and less than or equal to 10.

[0060] It has been found that bringing the first dilution channel arrangement 200 and fuel cup 204 into the aforementioned ratio and range provides significant benefits compared to dilution channel arrangements 200 and fuel cup 204 that do not fall within the aforementioned ratio and range. These benefits will be referenced in the following description. Figure 9 Describe it.

[0061] Figure 6 It shows from Figure 4 Line VI shows a partial cross-sectional side view of one of the multiple dilution channels 212. The channel centerline 234 of the shown dilution channel 212 extends radially outward from the fuel cup centerline 210, forming an outward dilution channel. The projection 236 of the channel centerline 234 relative to the fuel cup centerline 210 forms a first channel angle (β).

[0062] Figure 7 It shows from Figure 4 Line VII shows a partial cross-sectional side view of one of the multiple dilution channels 212. The channel centerline 234 of the shown dilution channel 212 extends radially inward toward the fuel cup centerline 210, forming an inward dilution channel. The projection 236 of the channel centerline 234 relative to the fuel cup centerline 210 forms a first channel angle (β).

[0063] The first channel angle (β) can be any suitable angle that is greater than or equal to -70 degrees and less than or equal to 70 degrees.

[0064] Although shown as a plurality of dilution channels 212 including an axial dilution channel 212, an outward dilution channel 212 and an inward dilution channel 212, it should be understood that the plurality of dilution channels 212 may be formed as an axial dilution channel 212 only, an outward dilution channel 212 only, an inward dilution channel 212 only, or any suitable combination thereof.

[0065] Figure 8 From Figure 4 The enlarged schematic front view of the dome wall 202 as seen in section VIII. As shown, the dilution channel 212 includes a section relative to the lateral reference line 270 (…). Figure 4 The projection 271 of the dilution channel 212 forms the corresponding channel centerline 234 of the second channel angle (θ). The second channel angle (θ) may have an absolute value greater than or equal to 0 degrees and less than or equal to 90 degrees. As a non-limiting example, the absolute value of the second channel angle (θ) of at least a portion of the dilution channel 212 may be greater than or equal to 0 degrees and less than or equal to 30 degrees. It should also be understood that at least a portion of the dilution channel 212 may be formed without a second channel angle (θ), such that they extend into the illustrated page and coincide with the slot 214, or otherwise surround the slot 214.

[0066] The slot flow (Fs) can flow outward from the slot 214. The slot flow (Fs) may include a second channel angle (θ) at the slot 214. Thus, the slot flow (Fs) can be defined by a circumferential component relative to the fuel cup centerline 210. The circumferential component of the slot flow (Fs) can be mixed with the fuel-air mixture (F1) ( Figure 4 The circumferential components are either aligned / parallel or opposite / not parallel.

[0067] Figure 9 yes Figure 4 A schematic front view of the dome wall 202, having the same Figure 4 Same view. The dilution channel arrangement 200 includes a region 213 containing grooves extending between relative interruptions 220, 222. Multiple grooves 214 ( Figure 4 One or more slots of any number are provided within each slotted area 213. During operation, a fuel-air mixture (F1) is ignited to define a flame 240, and a compressed gas flow is supplied through multiple dilution channels 212. The compressed gas flow forms a curtain around at least a portion of the circumferential extent of the flame 240. However, the flame 240 flows freely through a first interruption 220 and a second interruption 222 in the directions indicated by arrows 242 and 244, respectively.

[0068] Multiple fuel cups 204 ( Figure 4The fuel cups 204 are arranged circumferentially around the dome wall 202. Each fuel cup 204 may include a corresponding first dilution channel arrangement 200. The dilution channel arrangements 200 between fuel cups 204 may be the same or different. It is envisioned that a first interruption 220 of the first dilution channel arrangement 200 may be at least partially aligned with a second interruption 222 of a second dilution channel arrangement 200 circumferentially adjacent to the first dilution channel arrangement 200. The flame 240 propagated through the first interruption 220 of the first dilution channel arrangement 200 may meet and merge with the flame 240 propagated through the second interruption 222 of the second dilution channel arrangement 200. This merged flame 240 ensures the formation of a continuous annular flame ring along the dome wall 202, which ensures that the flame propagates from one fuel cup 204 to another and reduces the possibility of flameout at any given fuel cup 204.

[0069] Flow through groove 214 ( Figure 4 The compressed air flow can be defined by the total tank flow rate. The fuel-air mixture (F1) can be further defined by the total fuel cup flow rate. The total tank flow rate and the total fuel cup flow rate each flow freely through the corresponding tank 214 or fuel cup 204 for a period of time. Figure 4 The volume (e.g., ml / s) of the fluid (e.g., compressed air or fuel / air mixture, respectively) is defined. The ratio of total tank flow rate to total fuel cup flow rate can be greater than or equal to 0.2 and less than or equal to 4.

[0070] The compressed air curtain from dilution channel 212 is used for several reasons. First, the compressed air curtain prevents the flame 240 from contacting or otherwise overheating the dome wall 202, outer liner 206, and inner liner 208. This, in turn, ensures that the burners (e.g., outside the dome wall 202, outer liner 206, inner liner 208, or the dome wall 202, inner liner 208, or outer liner 206) are protected. Figure 3 The combustor 80) or gas turbine engine (e.g., Figure 1 No part of the gas turbine engine 10) is damaged or otherwise overheated by the flame 240. Second, a compressed air curtain is used to shape the flame 240. Flame shaping can be partially achieved through the first channel angle (β) ( Figure 6 and 7 ) or second channel angle (θ)( Figure 8 This is accomplished by, for example, by the outward dilution channel 212 ( Figure 6 This will allow flame 240 to expand, thereby generating flame 240 with a larger surface area, while diluting the inward channel 212 ( Figure 7 The flame 240 will be compressed or contracted to generate a flame 240 with a smaller surface area.

[0071] Furthermore, the orientation of the second channel angle (θ), or the inclusion of a second channel angle (θ), can be used to provide a hydrodynamic curtain of compressed air oriented relative to the fuel / air mixture (F1). It has been found that the orientation of the compressed air curtain can be used to shape and guide the flame 240. As a non-limiting example, when the circumferential component of the compressed air curtain is not parallel to the circumferential component of the fuel / air mixture (F1), the compressed air curtain is better adapted to guide the flame 240 away from the outer liner 206 and the inner liner 208. As a non-limiting example, when the circumferential component of the compressed air curtain is parallel to the circumferential component of the fuel / air mixture (F1), the compressed air curtain is better adapted to guide the flame 240 away from the dome wall 202. When the fuel / air mixture (F1) does not include a circumferential component, the compressed air curtain is used to swirl the fuel / air mixture in a desired manner.

[0072] Compressed air curtains can also be used to ensure the burner, including the first dilution channel arrangement 200 (e.g., Figure 2 The burner 80 can use fuels with high combustion temperatures and rapid flame speeds, such as hydrogen fuels. Because hydrogen fuels have significantly higher combustion temperatures than conventional hydrocarbon fuels, it becomes more important to isolate and cool the dome wall 202, outer liner 206, and inner liner 208. An air curtain generated by the first dilution channel arrangement 200 serves to provide an isolation layer (e.g., a compressed air curtain) between the flame 240 and the dome wall 202, outer liner 206, and inner liner 208, and to cool the dome wall 202, outer liner 206, and inner liner 208 and direct the flame 240 away from the dome wall 202, outer liner 206, and inner liner 208.

[0073] Imagine that a Rh2:Rh1 ratio greater than or equal to 1 and less than or equal to 3 results in the desired shape of the flame 240, which does not overheat the outer liner 206, inner liner 208, or dome wall 202, while still possessing the desired characteristics of the flame 240. For example, if the Rh2:Rh1 ratio is greater than 3, it has been found that the flame 240 relative to the fuel cup centerline 210 ( Figure 4 The flame expands radially outward and impacts the inner liner 208 and outer liner 206, causing overheating of the inner liner 208 and outer liner 206. However, if the Rh2:Rh1 ratio is less than 1, it has been found that the flame 240 is too concentrated around the central region defined by the fuel cup centerline 210, which in turn leads to an undesirable profile and pattern of the flame 240.

[0074] Imagine that the ratio of the slot width (Sw) to the width of the outlet 205 is greater than or equal to 0.03 and less than or equal to 0.3, creating multiple slots 214. These slots 214 have a sufficient compressed air flow rate relative to the flow rate of the fuel and air mixture (F1) flowing from the fuel cup 204 to produce the desired shape of the flame 240. If the ratio of the slot width (Sw) to the width of the outlet 205 is greater than 0.3, it has been found that excessive compressed air leaves the multiple slots 214, causing the flame 240 to have excessively high velocity or otherwise be overcompressed. However, if the ratio of the slot width (Sw) to the width of the outlet 205 is less than 0.03, it has been found that the compressed air leaving the multiple slots 214 is insufficient to form a compressed air curtain that isolates the dome wall 202, outer liner 206, and inner liner 208 from the heat of the flame 240, and the compressed air curtain also lacks sufficient force to shape the flame 240 into the desired pattern.

[0075] Imagine a ratio between the total axial length (La) and the slot width (Sw) greater than or equal to 0.1 and less than or equal to 10, resulting in a desired velocity of compressed air exiting multiple slots 214. For example, if the ratio between the total axial length (La) and the slot width (Sw) is greater than 10, the total axial length (La) is longer, meaning that the compressed air flowing through the dilution channel 212 will experience frictional losses, which ultimately reduce kinetic energy relative to the smaller total axial length (La). This reduction in kinetic energy due to frictional losses ultimately results in unsatisfactory burner performance compared to burners falling within the desired ratio of total axial length (La) to slot width (Sw). However, if the ratio between the total axial length (La) and the slot width (Sw) is less than 0.1, losses (e.g., drag losses) are found associated with the compressed air entering the combustion chamber and merging with the fuel and air mixture (F1) within the combustion chamber. These losses ultimately result in unsatisfactory burner performance compared to burners falling within the desired ratio of total axial length (La) to slot width (Sw).

[0076] Figure 10 It is suitable for use as Figure 4 A schematic cross-sectional view of an exemplary second dilution channel arrangement 300 of the first dilution channel arrangement 200. The second dilution channel arrangement 300 is similar to the first dilution channel arrangement 200, and therefore, similar portions will be identified by similar numbers increasing to the 300 series. It should be understood that, unless otherwise stated, the description of the first dilution channel arrangement 200 applies to the second dilution channel arrangement 300.

[0077] A second dilution channel arrangement 300 is disposed on a dome wall 302 and surrounds a fuel cup 304 having a fuel cup centerline 310. The dome wall 302 extends radially between an outer liner 306 and an inner liner 308. A plurality of dilution channels 312 extend through the dome wall 302 and terminate in a plurality of slots 314 formed along the dome wall 302. The second dilution channel arrangement 300 is disposed along a polar coordinate system 369 having a fuel cup reference line 372 extending from 0 degrees to 180 degrees and a transverse reference line 370 extending from 90 degrees to 270 degrees. The plurality of slots 314 extend at least along a first line 316 and a second line 318.

[0078] The second dilution channel arrangement 300 is similar to the first dilution channel arrangement 200, except that the radial distances of the first line 316 and the second line 318 from the fuel cup centerline 310 continuously increase from the first slot 315 to the second slot 317 of the plurality of slots 314. The first slot 315 and the second slot 317 may define the circumferential ends of the first line 316 or the second line 318 such that the radial distance along the respective first line 316 or the second line 318 increases from one circumferential end (e.g., the first slot 315 or the second slot 317) to a second circumferential end (e.g., the other of the first slot 315 or the second slot 317). The first slot 315 and the second slot 317 are located at the circumferentially opposite ends of the first line 316 and the second line 318. The first slot 315 is a first radial distance 358 from the fuel cup centerline 310. The second slot 317 is a second radial distance 360 ​​from the fuel cup centerline 310. The first radial distance 358 is less than the second radial distance 360. The radial distance of the grooves 314 in the circumferential direction between the first groove 315 and the second groove 317 can increase continuously or discontinuously, such that the first radial distance 358 is minimized and the second radial distance 360 ​​is maximized. This configuration can, for example, form a spiral pattern of grooves 314 along the dome wall 302.

[0079] The advantage of including a spiral pattern or a continuously increasing radial height is that the second dilution channel arrangement 300 can be used to further shape the flame exiting the fuel cup 304 (e.g., Figure 10 The flame 240), similar to how the second channel angle is used (e.g., Figure 8 The second channel angle (θ) is used to shape the flame. For example, the first line 316 and the second line 318 can form a spiral that extends circumferentially (e.g., from the first slot 315 to the second slot 317) parallel to or opposite to the circumferential direction of the fuel-air mixture (e.g., fuel-air mixture (F1)) leaving the fuel cup 304.

[0080] Figure 11 It is suitable for use as Figure 4A schematic cross-sectional view of an exemplary third dilution channel arrangement 400 of a first dilution channel arrangement 200. The third dilution channel arrangement 400 is similar to dilution channel arrangements 200 and 300. Figure 10 Therefore, similar parts will be identified by similar numbers in the 400 series. It should be understood that, unless otherwise stated, the descriptions of dilution channel arrangements 200 and 300 apply to the third dilution channel arrangement 400.

[0081] A third dilution channel arrangement 400 is disposed on a dome wall 402 and surrounds a fuel cup 404 having a fuel cup centerline 410. The dome wall 402 extends radially between an outer liner 406 and an inner liner 408. A plurality of dilution channels 412 extend through the dome wall 402 and terminate in a plurality of slots 414 formed along the dome wall 402. The third dilution channel arrangement 400 is disposed along a polar coordinate system 469 having a fuel cup reference line 472 extending from 0 degrees to 180 degrees and a transverse reference line 470 extending from 90 degrees to 270 degrees. The plurality of slots 414 extend at least along a first line 416 and a second line 418. The third dilution channel arrangement 400 includes a first interruption 420 and a second interruption 422.

[0082] The third dilution channel arrangement 400 is similar to dilution channel arrangements 200 and 300, except that the first line 416 and the second line 418 each include at least two non-parallel or non-uniform portions. As a non-limiting example, the first line 416 and the second line 418 each include a curve 462 and at least one linear line 464. The curve 462 may include two circumferential ends, and the at least one linear line 464 may extend outward from one of the two circumferential ends of the curve 462. As a non-limiting example, the first line 416 and the second line 418 each include a curve 462 and at least one linear line 464, the at least one linear line 464 including a first linear line extending from a first circumferential end of the curve 462 and a second linear line extending from a second circumferential end of the curve 462. The two linear lines 464 may each be formed identically or differently from each other. The linear line 464 may extend parallel to or not parallel to the transverse reference line 470. Any number of one or more slots may be present on the curve 462 and the linear line 464 of the first line 416 and the second line 418.

[0083] The linear line 464 may correspond to the extensions along the first interruption 420 and the second interruption 422, and extend radially outward from the corresponding portion of the corresponding curve 462 relative to the fuel cup centerline 410. In this way, the linear line 464 can form a channel for the first interruption 420 and the second interruption 422.

[0084] The grooves 414 disposed on the first line 416 and the second line 418 may each be defined by a corresponding cross-sectional area. The cross-sectional area of ​​the groove 414 may or may not be equal to the cross-sectional area of ​​the groove 414 on the second line 418. The cross-sectional area of ​​the groove 414 along the respective first line 416 and the second line 418 may be constant or different. As a non-limiting example, the groove 414 on the curve 462 may have a circular cross-sectional area, while the groove 414 on the linear line 464 may have an elliptical cross-sectional area. The elliptical cross-sectional area may be used to create elongated troughs extending along the first interruption 420 and the second interruption 422.

[0085] Figure 12 It is suitable for use as Figure 4 A schematic side view of an exemplary fourth dilution channel arrangement 500, corresponding to the first dilution channel arrangement 200. The fourth dilution channel arrangement 500 is similar to dilution channel arrangements 200 and 300. Figure 10 ), 400 Figure 11 Therefore, similar parts will be identified by similar numbers increasing to the 500 series. It should be understood that, unless otherwise stated, the descriptions of dilution channel arrangements 200, 300, and 400 apply to the fourth dilution channel arrangement 500.

[0086] A fourth dilution channel arrangement 500 is disposed on a dome wall 502 and surrounds a fuel cup 504 having a fuel cup centerline 510. The dome wall 502 extends radially between an outer liner 506 and an inner liner 508. A plurality of dilution channels 512 extend through the dome wall 502 and terminate in a plurality of slots 514 formed along the dome wall 502. The fourth dilution channel arrangement 500 is disposed along a polar coordinate system 569 having a fuel cup reference line 572 extending from 0 degrees to 180 degrees and a transverse reference line 570 extending from 90 degrees to 270 degrees. The plurality of slots 514 extend at least along a first line 516 and a second line 518. The fourth dilution channel arrangement 500 includes a first interruption 520 and a second interruption 522.

[0087] The fourth dilution channel arrangement 500 is similar to the third dilution channel arrangement 400 because it includes a first line 516 and a second line 518, each line being defined by a curve 562 and at least one linear line 564 (e.g., two linear lines 564). However, the difference lies in that at least one linear line 564 extends at an angle 566 relative to the lateral reference line 570. The absolute value of the angle 566 can be greater than or equal to 0 degrees and less than or equal to 60 degrees.

[0088] refer to Figure 11 and 12 The advantage of dilution channel arrangements of 400 or 500 is that they further guide and shape the flame (e.g., Figure 10(Flame 240). For example, the channels formed by linear lines 464, 564 can be used to guide the flame from one dilution channel arrangement 400, 500 to another circumferentially adjacent dilution channel arrangement 400, 500 or otherwise guide it to another circumferentially adjacent dilution channel arrangement 400, 500.

[0089] Figure 13 It is suitable for use as Figure 4 A schematic side view of an exemplary fifth dilution channel arrangement 600, corresponding to the first dilution channel arrangement 200. The fifth dilution channel arrangement 600 is similar to dilution channel arrangements 200 and 300. Figure 10 ), 400 Figure 11 ), 500 Figure 12 Therefore, similar parts will be identified by similar numbers increasing to the 600 series. It should be understood that, unless otherwise stated, the descriptions of dilution channel arrangements 200, 300, 400, and 500 apply to the fifth dilution channel arrangement 600.

[0090] A fifth dilution channel arrangement 600 is disposed on a dome wall 602 and surrounds a fuel cup 604 having a fuel cup centerline 610. The dome wall 602 extends radially between an outer liner 606 and an inner liner 608. A plurality of dilution channels 612 extend through the dome wall 602 and terminate in a plurality of slots 614 formed along the dome wall 602. The fifth dilution channel arrangement 600 is disposed along a polar coordinate system 669 having a fuel cup reference line 672 extending from 0 degrees to 180 degrees and a transverse reference line 670 extending from 90 degrees to 270 degrees. The plurality of slots 614 extend at least along a first line 616 and a second line 618.

[0091] For illustrative purposes, based on the trajectories of the first line 616 and the second line 618 at the outer slot 619, the first line 616 and the second line 618 are projected outwards beyond the outer slot 619 of the plurality of slots 614. As shown, the first line 616 and the second line 618 meet to form a continuous polygonal path around the fuel cup centerline 610. The polygonal path can be any suitable circular or non-circular path.

[0092] The first line 616 and the second line 618 may meet at two locations along the transverse reference line 670. Alternatively, the first line 616 and the second line 618 may meet at any suitable location along the dome wall 602.

[0093] Figure 14 It is suitable for use as Figure 4 A schematic side view of an exemplary sixth dilution channel arrangement 700, corresponding to the first dilution channel arrangement 200. The sixth dilution channel arrangement 700 is similar to dilution channel arrangements 200 and 300. Figure 10 ), 400 Figure 11 ), 500 Figure 12 ), 600 Figure 13 Therefore, similar parts will be identified by similar numbers increasing to the 700 series. It should be understood that, unless otherwise stated, the descriptions of dilution channel arrangements 200, 300, 400, 500, and 600 apply to the sixth dilution channel arrangement 700.

[0094] A sixth dilution channel arrangement 700 is disposed on a dome wall 702 and surrounds a fuel cup 704 having a fuel cup centerline 710. The dome wall 702 extends radially between an outer liner 706 and an inner liner 708. A plurality of dilution channels 712 extend through the dome wall 702 and terminate in a plurality of slots 714 formed along the dome wall 702. The sixth dilution channel arrangement 700 is disposed along a polar coordinate system 769 having a fuel cup reference line 772 extending from 0 degrees to 180 degrees and a transverse reference line 770 extending from 90 degrees to 270 degrees. The plurality of slots 714 extend at least along a first line 716 and a second line 718.

[0095] The sixth dilution channel arrangement 700 is similar to dilution channel arrangements 200, 300, 400, 500, and 600, except that the sixth dilution channel arrangement 700 is asymmetrical about both the lateral reference line 770 and the fuel cup reference line 772. The sixth dilution channel arrangement 700 may also include a plurality of slots 714 that are unevenly and unequally spaced along the dome wall 702. In other words, the sixth dilution channel arrangement 700 may include any randomly or non-randomly distributed slots 714 along the dome wall 702. As a non-limiting example, at least one slot 714 may be positioned along a tangent 777 extending from the fuel cup 204.

[0096] Figure 15 It is suitable for use as Figure 4 A schematic side view of an exemplary seventh dilution channel arrangement 800, corresponding to the first dilution channel arrangement 200. The seventh dilution channel arrangement 800 is similar to dilution channel arrangements 200 and 300. Figure 10 ), 400 Figure 11 ), 500 Figure 12 ), 600 Figure 13 ), 700 Figure 14 Therefore, similar parts will be identified by similar numbers in the 800 series. It should be understood that, unless otherwise stated, the descriptions of dilution channel arrangements 200, 300, 400, 500, 600, and 700 apply to the seventh dilution channel arrangement 800.

[0097] A seventh dilution channel arrangement 800 is disposed on a dome wall 802 and surrounds a fuel cup 804 having a fuel cup centerline 810. The dome wall 802 extends radially between an outer liner 806 and an inner liner 808. A plurality of dilution channels 812 extend through the dome wall 802. The seventh dilution channel arrangement 800 is disposed along a polar coordinate system 869, which has a fuel cup reference line 872 extending from 0 degrees to 180 degrees and a lateral reference line 870 extending from 90 degrees to 270 degrees.

[0098] The set of dilution channels 812 terminates at a first set of grooves 882 and a second set of grooves 884, each set of grooves being disposed on a first line 816 and a second line 818. The first set of grooves 882 may have a different formation relative to the second set of grooves 884. As a non-limiting example, each groove in the first set of grooves 882 may include a cross-sectional area larger or smaller than the cross-sectional area of ​​each groove in the second set of grooves 884. As a non-limiting example, each groove in the second set of grooves 884 may include a second channel angle (e.g., Figure 9 The second channel angle (θ) is not included in each of the first set of slots 882.

[0099] The first set of slots 882 and the second set of slots 884 may each be continuously arranged on appropriate portions of the first line 816 and the second line 818. As a non-limiting example, each first line 816 and second line 818 may have two separate sets of second slots 884. As a non-limiting example, the second sets of slots 884 may be arranged along the circumferentially distal ends of the first line 816 and the second line 818. It should be understood that the seventh dilution channel arrangement 800 may include any number of two or more sets of slots.

[0100] The advantage of the seventh dilution channel arrangement 800, including a first set of slots 882 and a second set of slots 884, is that the seventh dilution channel arrangement 800 allows for adjustment of the flame shape and cooling / isolation efficiency. As a non-limiting example, the second set of slots 884 may be disposed circumferentially at the distal ends of the first line 816 and the second line 818 and include a second channel angle. The first set of slots 882 may be circumferentially disposed between the second set of slots 884 and may be inward, outward, or axial slots without a second channel angle. Thus, as described herein, the second set of slots 884 can be used to provide a hydrodynamic air curtain consistent with or opposite to the fuel-air mixture, while the first set of slots 882 can be used for compressing or expanding the flame.

[0101] Figure 16 It is suitable for use as Figure 4 A schematic side view of an exemplary eighth dilution channel arrangement 900, corresponding to the first dilution channel arrangement 200. The eighth dilution channel arrangement 900 is similar to dilution channel arrangements 200 and 300. Figure 10 ), 400 Figure 11 ), 500 Figure 12 ), 600 Figure 13 ), 700 Figure 14 ), 800 Figure 15 Therefore, similar parts will be identified by similar numbers in the 900 series. It should be understood that, unless otherwise stated, the descriptions of dilution channel arrangements 200, 300, 400, 500, 600, 700, and 800 apply to the eighth dilution channel arrangement 900.

[0102] An eighth dilution channel arrangement 900 is disposed on a dome wall 902 and surrounds a fuel cup 904 having a fuel cup centerline 910. The dome wall 902 extends radially between an outer liner 906 and an inner liner 908. A plurality of dilution channels 912 extend through the dome wall 902. The eighth dilution channel arrangement 900 is disposed along a polar coordinate system 969 having a fuel cup reference line 972 extending from 0 degrees to 180 degrees and a lateral reference line 970 extending from 90 degrees to 270 degrees. The polar coordinate system 969 includes a first quadrant 974, a second quadrant 976, a third quadrant 978, and a fourth quadrant 980.

[0103] Similar to the seventh dilution channel arrangement 800, the eighth dilution channel arrangement 900 may include a first set of slots 982 and a second set of slots 984 disposed on the first line 916 and the second line 918. However, the difference is that the eighth dilution channel arrangement 900 also includes a third set of slots 986 disposed radially outward from the first set of slots 982 and the second set of slots 984 relative to the fuel cup centerline 910. This further forms a first row of slots 990 having the first set of slots 982 and the second set of slots 984 and following the first line 916 and the second line 918, and a second row of slots 992 having the third set of slots 986 and following the third line 988.

[0104] The third set of slots 986 may or may not correspond to the first set of slots 982 or the second set of slots 984. The third line 988 may extend linearly or non-linearly and may be parallel or not parallel to the transverse reference line 970. The second row of slots 992 may include a total of four third set of slots 986. As a non-limiting example, one third set of slots 986 may be provided in each of the first quadrant 974, the second quadrant 976, the third quadrant 978, and the fourth quadrant 980.

[0105] The advantage of having a first row of grooves 990 and a second row of grooves 992 is that it further shapes the flame (e.g., Figure 9 The flame 240) prevents the flame from escaping through the compressed air curtain generated by the first row of slots 990 and the second row of slots 992, and heats the outer liner (e.g., Figure 4 Outer lining 206), inner lining (e.g., Figure 4 The inner lining 208) or the dome wall 902.

[0106] The benefits of this disclosure include burners suitable for use with hydrogen-containing fuels. As previously mentioned, hydrogen-containing fuels have higher flame temperatures than conventional fuels (e.g., non-hydrogen-containing fuels). That is, hydrogen or hydrogen-blended fuels generally have a wider combustible range and faster combustion rates than conventional fuels (such as petroleum-based fuels, or mixtures of petroleum and synthetic fuels). These high combustion temperatures of hydrogen-containing fuels mean that additional isolation is required between the ignited hydrogen-containing fuel and the surrounding components of the gas turbine engine (e.g., dome walls, inner / outer liners, and other parts of the gas turbine engine). As described herein, the burner includes multiple slots that form an isolation layer (e.g., a compressed air curtain) between the ignited hydrogen-containing fuel and the dome walls, inner / outer liners, and any parts of the gas turbine engine outside the dome walls, inner / outer liners, and outer liners. The compressed air curtain is further used to shape the flame within the combustion chamber, which in turn leads to enhanced control of the flame shape profile. By shaping the flame, the liner wall temperature, dome wall temperature, burner outlet temperature profile, and the pattern of the flame / gas exiting the burner can be controlled. This control or shaping can further ensure that the combustion zone or other hot zones of the turbine engine do not fail or otherwise become ineffective due to overheating, thereby increasing the turbine engine's lifespan. Furthermore, as described herein, the introduction of a dilution channel arrangement ensures uniform, consistent, or otherwise desired flame propagation within the combustor.

[0107] Compared to conventional fuels, the benefits associated with using hydrogen fuels include more environmentally friendly engines because hydrogen fuels produce fewer carbon pollutants when burned than combustors using conventional fuels. For example, a combustor using 100% hydrogen fuel (e.g., 100% H2) would have zero carbon pollutants. As described in this article, combustors can be used in situations involving 100% hydrogen fuel.

[0108] Further benefits associated with using hydrogen fuel compared to conventional fuels include the ability of gas turbine engines to achieve the same turbine inlet temperature with less fuel due to the higher calorific value of the fuel. For example, a conventional gas turbine engine using conventional fuels would require more fuel to produce the same work or engine output as this gas turbine engine using hydrogen fuel. This means that, compared to a conventional gas turbine engine, less fuel can be used to generate the same engine output, or the same amount of fuel can be used to generate an excessively increased engine output.

[0109] Within the scope not described herein, different features and structures of various 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.

[0110] This written description uses examples to illustrate aspects of the disclosure described herein, including best practices, and also enables any person skilled in the art to practice aspects of this disclosure, including making and using any apparatus or system and methods of making any combinations. The patentable scope of aspects of this disclosure is defined by the claims, and may include other examples that would occur to a person skilled in the art. Such other examples are intended to fall within the scope of the claims if they have structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

[0111] Further details are provided by the following topics:

[0112] A combustor for a gas turbine engine, the combustor defining a combustor centerline and comprising: a dome wall; an annular bushing extending from the dome wall; a combustion chamber defined at least partially by the dome wall and the annular bushing; a set of fuel cups circumferentially spaced relative to the combustor centerline along the dome wall, wherein each fuel cup has a fuel cup centerline; a set of dilution channels for each of the fuel cups, wherein each dilution channel has a channel centerline; and a plurality of slots spaced around the fuel cups, wherein each slot defines an end of at least one dilution channel and includes a center point defined as the location where the channel centerline of the at least one dilution channel intersects the slot. The center points of the plurality of slots are located in a polar coordinate system having: a fuel cup reference line extending through the fuel cup centerline and defining a reference line from 0 degrees to 180 degrees, wherein 0 degrees is radially closest to the burner centerline; a lateral reference line defining a reference line from 90 degrees to 270 degrees; a first quadrant extending between 0 degrees and 90 degrees; a second quadrant extending between 90 degrees and 180 degrees; a third quadrant extending between 180 degrees and 270 degrees; and a fourth quadrant extending between 270 degrees and 360 degrees; wherein opposing interruptions are defined by slotless arc segments at + / - 75 degrees to the lateral reference line, and opposing slotted arc segments lie between the slotless arc segments, wherein the plurality of slots are located in the slotted arc segments and not in the slotless arc segments.

[0113] A burner defining a burner centerline, the burner comprising: a dome wall; an annular bushing extending from the dome wall; a combustion chamber at least partially defined by the dome wall and the annular bushing; a set of fuel cups circumferentially spaced relative to the burner centerline along the dome wall, wherein each fuel cup has a fuel cup centerline; a set of dilution channels for each of the fuel cups, wherein each dilution channel has a channel centerline; and a plurality of slots spaced around the fuel cups, wherein each slot defines an end of at least one dilution channel and includes a center point defined as the location where the channel centerline of the at least one dilution channel intersects the slot, wherein the plurality of slots... The center point is located in a polar coordinate system having: a fuel cup reference line extending through the fuel cup centerline and defining a reference line from 0 degrees to 180 degrees, wherein 0 degrees is radially closest to the burner centerline; a lateral reference line defining a reference line from 90 degrees to 270 degrees; a first quadrant extending between 0 degrees and 90 degrees; a second quadrant extending between 90 degrees and 180 degrees; a third quadrant extending between 180 degrees and 270 degrees; and a fourth quadrant extending between 270 degrees and 360 degrees; wherein opposing interruptions are defined by grooveless arc segments at + / - 75 degrees to the lateral reference line, and opposing slotted arc segments are located between the grooveless arc segments, wherein the plurality of slots are located in the slotted arc segments and are not present in the grooveless arc segments.

[0114] According to any of the preceding clauses, the centerline of the channel forms a first channel angle with respect to the centerline of the fuel cup, wherein the first channel angle is greater than or equal to -70 degrees and less than or equal to 70 degrees.

[0115] According to any of the preceding clauses, the burner includes a first dilution channel having a first channel angle and a second dilution channel having a first channel angle that is not equal to the first channel angle of the first dilution channel.

[0116] According to any of the foregoing clauses, each dilution channel includes a corresponding first channel angle that is not equal to each of the other first channel angles.

[0117] The burner according to any of the foregoing clauses, wherein the plurality of slots includes a first row of slots disposed along a first line and a second row of slots positioned radially outward from the first row of slots and disposed along a second line, the second line being separate from the first line.

[0118] According to any of the foregoing clauses, the burner wherein the second line is linear.

[0119] According to any of the foregoing clauses, the burner wherein the second line forms a 0-degree angle with respect to the lateral reference line.

[0120] According to any of the preceding clauses, the burner wherein the second line forms an angle relative to the lateral reference line, the angle having an absolute value greater than 0 degrees and less than or equal to 60 degrees.

[0121] According to any of the foregoing clauses, the burner wherein the first line is non-linear.

[0122] According to any of the foregoing clauses, the first channel angle of the plurality of slots disposed on the first line is greater than the first channel angle of the plurality of slots disposed on the second line.

[0123] The burner according to any of the foregoing clauses, wherein the plurality of slots extend between at least two adjacent quadrants.

[0124] According to any of the preceding clauses, the plurality of slots are arranged along a first line, and each of the plurality of slots on the first line is arranged at a radial distance from the center line of the fuel cup, wherein the radial distance increases continuously from one circumferential end of the first line to the other circumferential end of the first line.

[0125] According to any of the foregoing clauses, a first subset of the plurality of slots follows a curve, and a second subset of the slots follows a linear line extending from the circumferential end of the curve, wherein the linear line corresponds to at least one of the opposing interruptions.

[0126] According to any of the preceding clauses, the burner wherein the linear line forms an angle relative to the transverse reference line, the angle having an absolute value greater than or equal to 0 degrees and less than or equal to 70 degrees.

[0127] According to any of the foregoing clauses, the plurality of slots are asymmetrical about the corresponding fuel cup reference lines.

[0128] According to any of the preceding clauses, the burner wherein the plurality of slots follow a first line and a second line separate from the first line, wherein the first line and the second line are symmetrical or asymmetrical with respect to at least one of the fuel cup reference line or the transverse reference line.

[0129] According to any of the preceding clauses, the set of dilution channels forms a dilution channel arrangement around each of the set of fuel cups, wherein at least two dilution channels are arranged differently from each other.

[0130] According to any of the foregoing clauses, the burner wherein the plurality of slots follow a non-circular polygonal path extending circumferentially around the centerline of the fuel cup.

[0131] According to any of the foregoing clauses, the combustor wherein the set of fuel cups receives a fuel stream comprising hydrogen-containing fuel.

[0132] According to any of the preceding clauses, the center point of each of the plurality of slots is positioned at a first radial height from the centerline of the fuel cup, each of the set of fuel cups includes an outlet formed along the dome wall, wherein the radially outer surface of the outlet is positioned at a second radial height from the centerline of the fuel cup, and the ratio between the first radial height and the second radial height is greater than 1 and less than or equal to 3.

[0133] According to any of the preceding clauses, the burner wherein, when viewed along a vertical plane perpendicular to the centerline of the corresponding fuel cup and intersecting the corresponding slot, each of the plurality of slots includes a slot width, each of the set of fuel cups includes an outlet formed along the dome wall, the outlet having an outlet width, and the ratio between the slot width and the outlet width is greater than or equal to 0.03 and less than or equal to 0.5.

[0134] According to any of the preceding clauses, a fuel / air mixture is supplied to the combustion chamber through the set of fuel cups, wherein a portion of the fuel / air mixture is supplied through a corresponding fuel cup in the set of fuel cups at a fuel / air volumetric flow rate, and compressed air is supplied to the combustion chamber through a corresponding set of dilution channels at a compressed air volumetric flow rate, wherein the ratio between the fuel / air volumetric flow rate and the compressed air volumetric flow rate is greater than or equal to 0.2 and less than or equal to 4.

[0135] According to any of the preceding clauses, each of the plurality of dilution channels includes a total axial length between the inlet of the dilution channel and the corresponding slot, the corresponding slot including a slot width when viewed along a vertical plane perpendicular to the centerline of the corresponding fuel cup and intersecting the corresponding slot, and wherein the ratio between the total axial length and the slot width is greater than or equal to 0.1 and less than or equal to 10.

Claims

1. A combustor for a gas turbine engine, characterized in that, The burner defines a burner centerline and includes: Dome wall; An annular bushing extending from the dome wall; A combustion chamber, which is at least partially defined by the dome wall and the annular bushing; A set of fuel cups, the set of fuel cups being circumferentially spaced relative to the burner centerline along the dome wall, wherein each fuel cup has a fuel cup centerline; and A set of dilution channels for each of the set of fuel cups, wherein each set of dilution channels terminates in a plurality of slots spaced apart around the corresponding fuel cup in the set of fuel cups, wherein each of the set of dilution channels has a channel centerline terminating at the center point of the center point of the corresponding slot in the plurality of slots, the center point of the respective slot being located in a polar coordinate system having: Fuel cup reference line, which extends through the center line of the fuel cup and defines a reference line from 0 degrees to 180 degrees, wherein 0 degrees is radially closest to the center line of the burner. Horizontal reference line, which defines a reference line from 90 degrees to 270 degrees; The first quadrant extends between 0 degrees and 90 degrees; The second quadrant extends between 90 degrees and 180 degrees; The third quadrant, which extends between 180 degrees and 270 degrees; and The fourth quadrant extends between 270 degrees and 360 degrees; The opposite interruption is defined by a slotless arc segment at + / - 75 degrees to the transverse reference line, and the opposite slotted arc segments are located between the slotless arc segments, wherein the plurality of slots are located in the slotted arc segments and are not present in the slotless arc segments.

2. The burner according to claim 1, characterized in that, in, The centerline of the channel forms a first channel angle relative to the centerline of the fuel cup, wherein the first channel angle is greater than or equal to -70 degrees and less than or equal to 70 degrees.

3. The burner according to claim 2, characterized in that, in, The set of dilution channels includes a first dilution channel having a first channel angle and a second dilution channel having a first channel angle that is not equal to the first channel angle.

4. The burner according to claim 2, characterized in that, in, Each dilution channel includes a corresponding first channel angle that is not equal to each of the other first channel angles.

5. The burner according to claim 2, characterized in that, in, The plurality of slots includes a first row of slots arranged along a first line and a second row of slots positioned radially outward from the first row of slots and arranged along a second line, the second line being separate from the first line.

6. The burner according to claim 5, characterized in that, in, The second line is linear.

7. The burner according to claim 6, characterized in that, in, The second line forms a 0-degree angle with respect to the horizontal reference line.

8. The burner according to claim 6, characterized in that, in, The second line forms an angle relative to the horizontal reference line, the angle having an absolute value greater than 0 degrees and less than or equal to 60 degrees.

9. The burner according to claim 6, characterized in that, in, The first line is non-linear.

10. The burner according to claim 5, characterized in that, in, The first channel angle of the plurality of slots disposed on the first line is greater than the first channel angle of the plurality of slots disposed on the second line.

11. The burner according to any one of claims 1-10, characterized in that, in, The plurality of slots extend between at least two adjacent quadrants.

12. The burner according to claim 1, characterized in that, in, The plurality of slots are arranged along a first line, and each of the plurality of slots on the first line is arranged at a radial distance from the center line of the fuel cup, wherein the radial distance increases continuously from one circumferential end of the first line to the other circumferential end of the first line.

13. The burner according to claim 1, characterized in that, in, A first subset of the plurality of slots follows a curve, and a second subset of the slots follows a linear line extending from the circumferential end of the curve, wherein the linear line corresponds to at least one of the opposing interruptions.

14. The burner according to claim 13, characterized in that, in, The linear line forms an angle relative to the transverse reference line, the angle having an absolute value greater than or equal to 0 degrees and less than or equal to 70 degrees.

15. The burner according to any one of claims 1-10, characterized in that, in, The multiple slots are asymmetrical about their corresponding fuel cup reference lines.

16. The burner according to any one of claims 1-10, characterized in that, in, The plurality of grooves follow a first line and a second line separate from the first line, wherein the first line and the second line are symmetrical or asymmetrical with respect to at least one of the fuel cup reference line or the lateral reference line.

17. The burner according to any one of claims 1-10, characterized in that, in, The set of dilution channels forms a dilution channel arrangement around each of the set of fuel cups, wherein at least two dilution channels are arranged differently from each other.

18. The burner according to any one of claims 1-10, characterized in that, in, The plurality of slots follow a non-circular polygonal path that extends circumferentially around the center line of the fuel cup.

19. The burner according to any one of claims 1-10, characterized in that, in, The set of fuel cups receives a fuel stream including hydrogen-containing fuel.

20. A burner defining a burner centerline, characterized in that, The burner includes: Dome wall; An annular bushing extending from the dome wall; A combustion chamber, which is at least partially defined by the dome wall and the annular bushing; A set of fuel cups, the set of fuel cups being circumferentially spaced along the dome wall relative to the burner centerline, wherein each fuel cup has a fuel cup centerline; A set of dilution channels for each of the set of fuel cups, wherein each of the set of dilution channels has a channel centerline; and A plurality of slots spaced apart around fuel cups in a set of fuel cups, wherein each of the plurality of slots defines the end of at least one dilution channel in the set of dilution channels and includes a center point defined as the location where the centerline of the at least one dilution channel intersects the slot, wherein the center point of the plurality of slots is located in a polar coordinate system having: Fuel cup reference line, which extends through the center line of the fuel cup and defines a reference line from 0 degrees to 180 degrees, wherein 0 degrees is radially closest to the center line of the burner. Horizontal reference line, which defines a reference line from 90 degrees to 270 degrees; The first quadrant extends between 0 degrees and 90 degrees; The second quadrant extends between 90 degrees and 180 degrees; The third quadrant, which extends between 180 degrees and 270 degrees; and The fourth quadrant extends between 270 degrees and 360 degrees; The opposite interruption is defined by a slotless arc segment at + / - 75 degrees to the transverse reference line, and the opposite slotted arc segments are located between the slotless arc segments, wherein the plurality of slots are located in the slotted arc segments and are not present in the slotless arc segments.

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