Combustor liner having dilution openings with swirl vanes

Abstract

A combustor liner for a gas turbine includes a liner that at least partially defines a combustion chamber and has a plurality of dilution openings therethrough. Each dilution opening includes an outer wall that defines an outer periphery of the dilution opening and defines a dilution opening centerline axis passing through the dilution opening. A plurality of swirl vanes extend from the outer wall into a dilution airflow passage, the dilution airflow passage extending through the dilution opening. Each of the plurality of swirl vanes extends from the outer wall into the dilution airflow passage at a respective swirl vane angle relative to the outer wall. The plurality of swirl vanes are arranged in a continuous arrangement about the outer wall, and consecutive respective swirl vanes of the plurality of swirl vanes extend from the outer wall at different swirl vane angles.

Description

Technical Field

[0001] The present disclosure relates to combustor liners with dilution. More particularly, the present disclosure relates to dilution openings with swirl vanes. Background Art

[0002] In conventional gas turbine engines, it is known to provide a dilution air flow into the combustion chamber downstream of the primary combustion zone. Typically, the combustor includes a liner that defines the combustion chamber. The liner may include dilution holes that provide an air flow (i.e., a dilution jet) from a passage around the liner into the combustion chamber. Some applications are known to use circular holes to provide a dilution flow to the combustion chamber. The air flow through the circular dilution holes in conventional combustors mixes with the combustion gases in the combustion chamber to provide a quenching of the combustion gases. The high temperature region seen behind the dilution jet (i.e., in the wake region of the dilution jet) is associated with high nitrous oxide (NO x ) is associated. In addition, the circular dilution holes do not diffuse the dilution air flow laterally, which would create high temperatures between the dilution holes, which also contributes to higher NO x form. BRIEF DESCRIPTION OF THE DRAWINGS

[0003] Features and advantages of the present disclosure will be apparent from the following description of various exemplary embodiments, as illustrated in the drawings, in which like reference numerals generally indicate identical, functionally similar, and / or structurally similar elements.

[0004] Figure 1 is a schematic partial cross-sectional side view of an exemplary high bypass turbofan jet engine according to aspects of the present disclosure.

[0005] Figure 2 is a partial cross-sectional side view of an exemplary combustor according to aspects of the present disclosure.

[0006] Figure 3 According to aspects of the present disclosure Figure 2 A plan view of the cold surface side of the multiple dilution openings taken at view AA.

[0007] Figure 4 is an alternative plan view of the cold surface side of a plurality of dilution openings according to another aspect of the present disclosure.

[0008] Figure 5 According to aspects of the present disclosure Figure 3 Detailed view of the dilution opening taken at 100.

[0009] Figure 6 According to aspects of the present disclosure Figure 5 A view of the outer wall and swirl vanes taken at view BB in FIG.

[0010] Figure 7According to another aspect of the present disclosure Figure 5 A view of the outer wall and swirl vanes taken at view BB in FIG.

[0011] Figure 8 According to another aspect of the present disclosure Figure 5 A view of the outer wall and swirl vanes taken at view BB in FIG.

[0012] Figure 9 According to aspects of the present disclosure Figure 7 A partial cross-sectional view through the swirl vane taken at plane 9-9 of FIG.

[0013] Figure 10 According to aspects of the present disclosure Figure 7 A partial cross-sectional view through the swirl vane taken at plane 10-10 of FIG.

[0014] Figure 11 According to aspects of the present disclosure Figure 7 A partial cross-sectional view through the swirl vane taken at plane 11-11 of FIG.

[0015] Figure 12 According to another aspect of the present disclosure Figure 3 Detailed view of the dilution opening taken at 100.

[0016] Figure 13 According to another aspect of the present disclosure Figure 3 Detailed view of the dilution opening taken at 100.

[0017] Figure 14 According to aspects of the present disclosure Figure 2 An enlarged view of an alternative liner and dilution opening arrangement is taken at detail view 304 of FIG.

[0018] Figure 15 According to aspects of the present disclosure Figure 2 An enlarged view of another alternative liner and dilution opening arrangement is taken at detail view 304 of FIG.

[0019] Figure 16 According to aspects of the present disclosure Figure 2 An enlarged view of yet another alternative liner and dilution opening arrangement is shown taken at detail view 304 of FIG. DETAILED DESCRIPTION

[0020] Features, advantages and embodiments of the present disclosure are set forth or apparent by considering the following detailed description, drawings and claims. In addition, it should be understood that the following detailed description is exemplary and is intended to provide further explanation, rather than limiting the scope of the present disclosure as claimed.

[0021] Various embodiments are discussed in detail below. Although specific embodiments are discussed, this is for illustrative purposes only. Those skilled in the relevant art will recognize that other components and configurations may be used without departing from the spirit and scope of the present disclosure.

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

[0023] The terms "upstream" and "downstream" refer to relative directions of fluid flow in a fluid path. For example, "upstream" refers to the direction from which the fluid is flowing, and "downstream" refers to the direction toward which the fluid is flowing.

[0024] In the combustion section of a turbine engine, the airflow in the outer passage surrounding the combustor liner is diverted through dilution holes in the combustor liner and into the combustion chamber to serve as dilution air. One purpose of the dilution air is to quench (i.e., cool) the combustion gases in the combustion chamber before the gases enter the turbine section downstream of the combustion chamber. At the leading edge of the dilution hole, airflow separation occurs, causing very little dilution air to adhere to the upstream side of the dilution hole. This separation also causes hot gases to be drawn into the dilution flow passage within the dilution hole, thereby shortening the life of the liner. At the trailing edge of the dilution hole along the inner surface of the liner (i.e., inside the combustion chamber), a wake is formed in the dilution airflow behind the dilution hole. The wake causes the temperature behind the dilution airflow to be higher, resulting in more NO x is formed, and this shortens the life of the combustor liner.

[0025] The present disclosure provides a method for filling the wake region at the downstream side of the dilution hole with dilution air, thereby reducing NO x Discharge and improve liner durability. According to the present disclosure, a dilution opening includes a plurality of swirl vanes arranged about an outer wall of the dilution opening. Respective swirl vanes in the plurality of swirl vanes are arranged at different swirl vane angles relative to the wall of the dilution opening and relative to each other. The respective different swirl vane angles provide preferential swirl of dilution air passing through the dilution opening to fill a wake region at a downstream side of the dilution opening. A specific swirl vane angle for each swirl vane can be selected based on a desired preferential swirl and based on the incoming air flow through the outer flow channel.

[0026] Referring now to the accompanying drawings, Figure 1is a schematic partial cross-sectional side view of an exemplary high bypass turbofan jet engine 10 (referred to herein as "engine 10") that may incorporate various embodiments of the present disclosure. Although further described below with reference to a turbofan engine, the present disclosure is also applicable to turbomachinery in general, including turbojets, turboprops, and turboshaft gas turbine engines, including marine turbine engines, industrial turbine engines, and auxiliary power units. Figure 1 As shown, for reference, the engine 10 has an axial centerline axis 12 extending therethrough from an upstream end 98 to a downstream end 99. Generally, the engine 10 may include a fan assembly 14 and a core engine 16 disposed downstream of the fan assembly 14.

[0027] The core engine 16 may generally include an outer casing 18 defining an annular inlet 20. The outer casing 18 surrounds or at least partially forms, in serial flow relationship: a compressor section (22 / 24) having a low pressure (LP) compressor 22 and a high pressure (HP) compressor 24; a combustor 26; a turbine section (28 / 30) including a high pressure (HP) turbine 28 and a low pressure (LP) turbine 30; and an ejection exhaust nozzle section 32. A high pressure (HP) rotor shaft 34 drivingly connects the HP turbine 28 to the high pressure compressor 24. A low pressure (LP) rotor shaft 36 drivingly connects the LP turbine 30 to the LP compressor 22. The LP rotor shaft 36 may also be connected to a fan shaft 38 of the fan assembly 14. In certain embodiments, as shown Figure 1 As shown, the LP rotor shaft 36 may be connected to the fan shaft 38 via a reduction gear 40 , such as in an indirect drive or gear drive configuration.

[0028] like Figure 1 As shown, the fan assembly 14 includes a plurality of fan blades 42 coupled to and extending radially outward from the fan shaft 38. An annular fan casing or nacelle 44 circumferentially surrounds the fan assembly 14 and / or at least a portion of the core engine 16. The nacelle 44 may be supported relative to the core engine 16 by a plurality of circumferentially spaced outlet guide vanes or struts 46. In addition, at least a portion of the nacelle 44 may extend over an outer portion of the core engine 16 to define a bypass airflow passage 48 therebetween.

[0029] Figure 2 Yes Figure 1 A cross-sectional side view of an exemplary combustor 26 of the core engine 16 is shown. Figure 2 The exemplary combustor 26 shown in FIG is depicted as an annular combustor including both an inner liner and an outer liner each extending circumferentially about a combustor centerline axis, but the present disclosure may be implemented in other types of combustors, including, for example, can-type combustors. Figure 2As shown, the combustor 26 may generally include a combustor liner 50 having an inner liner 52 and an outer liner 54, and a dome assembly 56, which together define a combustion chamber 62. The inner liner 52 and the outer liner 54 may each extend circumferentially about a combustor centerline axis 112, which may correspond to the engine axial centerline axis 12. Although Figure 2 A single-layer liner is depicted for both the inner liner 52 and the outer liner 54, but other types of liners, such as multi-layer liners, may be included instead. The inner liner 52 and the outer liner 54 are connected to a cover 60, and a pressure chamber 66 is defined between the cover 60, the inner liner 52, the outer liner 54, and the dome assembly 56.

[0030] like Figure 2 As shown, the inner liner 52 is enclosed within the inner casing 65, and the outer liner 54 is enclosed within the outer casing 64. An outer flow passage 88 is defined between the outer liner 54 and the outer casing 64, and an inner flow passage 90 is defined between the inner liner 52 and the inner casing 65. Both the outer casing 64 and the inner casing 65 can extend circumferentially about the combustor centerline axis 112. The cold surface side 53 of the inner liner 52 is adjacent to the inner flow passage 90, and the hot surface side 55 of the inner liner 52 is adjacent to the combustion chamber 62. Similarly, the cold surface side 57 of the outer liner 54 is adjacent to the outer flow passage 88, and the hot surface side 59 of the outer liner 54 is adjacent to the combustion chamber 62. The inner liner 52 and the outer liner 54 can extend from the dome assembly 56 to the HP turbine 28 ( Figure 1 ) inlet, thereby at least partially defining a hot gas path between the combustor liner 50 and the HP turbine 28. More specifically, the combustion chamber 62 may more particularly define a primary combustion zone 74 where an initial chemical reaction of the fuel-oxidant mixture 72 occurs to produce combustion gases 86, and / or where recirculation of the combustion gases 86 may occur before the combustion gases 86 flow further downstream to the dilution zone 75. At the dilution zone 75, the combustion gases 86 mix with dilution air 82(c) before flowing to the secondary combustion zone 77 and entering the turbine nozzle 79 at the inlet of the HP turbine 28 and the LP turbine 30. As will be described in more detail below, the plurality of dilution openings 68 and the plurality of dilution openings 69 provide a flow of dilution air 82(c) therethrough and into the combustion chamber 62. The dilution air 82 ( c ) flow may thus be used to provide quenching of the combustion gases 86 in the dilution zone 75 downstream of the primary combustion zone 74 , thereby cooling the flow of combustion gases 86 entering the turbine section ( 28 / 30 ).

[0031] During operation of the engine 10, as Figure 1 and Figure 2As shown collectively, a quantity of air (schematically indicated by arrow 73) enters engine 10 from upstream end 98 through nacelle 44 and / or associated nacelle inlet 76 of fan assembly 14. As air 73 passes through fan blades 42, a portion of air 73 is directed or channeled into bypass airflow passage 48 as bypass airflow 78, while another portion of air 73 is directed or channeled into LP compressor 22 as compressor inlet air 80. Compressor inlet air 80 is progressively compressed as it flows through LP compressor 22 and HP compressor 24 toward combustor 26. Figure 2 As shown, compressed air 82 flows into and pressurizes the diffuser chamber 84. A first portion of the compressed air 82 (as schematically indicated by arrow 82(a)) flows from the diffuser chamber 84 into the pressure plenum 66, where the first portion of the compressed air 82 is mixed with fuel provided by the fuel nozzle assembly 70 through the mixer assembly 58. The fuel-oxidizer mixture 72 is then injected into the combustion chamber 62 through the mixer assembly 58 in the mixer swirl direction 63 about the mixer assembly centerline axis 61. The fuel-oxidizer mixture 72 is ignited and combusted to produce combustion gases 86 within the primary combustion zone 74 of the combustion chamber 62. Typically, the LP compressor 22 and the HP compressor 24 provide more compressed air 82 to the diffuser chamber 84 than is required for combustion. Therefore, a second portion of the compressed air 82 (as schematically indicated by arrow 82(b)) can be used for various purposes other than combustion. For example, Figure 2 As shown, compressed air 82(b) can be directed into outer flow passage 88 and generally flow downstream in flow direction 85 within outer flow passage 88. Similarly, a portion of compressed air 82(b) can be directed into inner flow passage 90 and generally flow downstream in flow direction 87 within inner flow passage 90. A portion of compressed air 82(b) that passes through dilution openings 68 and through dilution openings 69 (schematically indicated by arrows 82(c)) can be directed through the plurality of dilution openings 68 and the plurality of dilution openings 69 into the dilution zone 75 of the combustion chamber 62 to provide quenching of the combustion gases 86 in the dilution zone 75. The dilution air 82(c) flowing through the plurality of dilution openings 68 and the plurality of dilution openings 69 can also provide turbulence to the flow of combustion gases 86, thereby providing better mixing of the dilution air 82(c) with the combustion gases 86. Additionally, or in the alternative, at least a portion of the compressed air 82 ( b ) may be directed out of the diffuser cavity 84 for other purposes, such as providing cooling air for at least one of the HP turbine 28 or the LP turbine 30 .

[0032] Reference again Figure 1 and Figure 2 , the combustion gases 86 produced in the combustion chamber 62 flow into the HP turbine 28, thereby causing the HP rotor shaft 34 to rotate, thereby supporting the operation of the HP compressor 24. Figure 1As shown, combustion gases 86 are then directed through LP turbine 30, thereby causing LP rotor shaft 36 to rotate, thereby supporting operation of LP compressor 22 and / or rotation of fan shaft 38. Combustion gases 86 are then exhausted through jet exhaust nozzle section 32 of core engine 16 to provide propulsion at downstream end 99.

[0033] Figure 3 According to aspects of the present disclosure Figure 2 8 is a plan view of a portion of the cold surface side 57 through the plurality of dilution openings 68 of the outer liner 54 taken at view AA of FIG. Figure 3 The arrangement of the outer sleeve 54 is also applicable to the plurality of dilution openings 69 through the inner sleeve 52, and therefore, references to the various inner sleeve components may be included in parentheses in the drawings. However, for the sake of brevity, the following description will be directed to the components of the outer sleeve 54. Figure 3 , a plurality of dilution openings 68 are shown as being spaced apart from one another in the circumferential direction (C). Figure 3 As shown, the plurality of dilution openings 68 are arranged along the same longitudinal position 102 in the longitudinal direction (L) of the outer liner 54. The longitudinal position 102 of the plurality of dilution openings 68 may be a given distance 103 ( Figure 2 The compressed air 82(b) flowing in the flow direction 85 within the outer flow passage 88 flows over the cold surface side 57 of the outer liner 54, and some of the compressed air 82(b) flows through each of the plurality of dilution openings 68 into the combustion chamber 62 as dilution air 82(c) ( Figure 2 ). With reference to the flow direction 85, the dilution opening 68 includes an upstream side 108 that receives the incoming compressed air 82(b) and a downstream side 110.

[0034] Figure 4 1 shows the cold surface side 57 through the plurality of dilution openings 68 of the outer liner 54 according to another aspect of the present disclosure. Figure 3 An alternative plan view of a configuration in which multiple dilution openings 68 are arranged at the same longitudinal position 102 Figure 3 Compared with Figure 4 In an aspect of the present invention, a first group 105 of the plurality of dilution openings 68 can be staggered relative to a second group 107 of dilution openings 68. For example, the plurality of dilution openings 68 can be staggered such that the first group 105 of dilution openings 68 is arranged at a first longitudinal position 102 and the second group 107 of dilution openings 68 is arranged at a second longitudinal position 104. The longitudinal positions 102 and the second longitudinal positions 104 can be offset by a given amount 106. Furthermore, the plurality of dilution openings 68 can be staggered in an alternating arrangement in the circumferential direction (C).

[0035] Figure 5 According to aspects of the present disclosure Figure 3100 of the dilution opening 68. The dilution opening 68 includes an outer wall 114 that defines an outer perimeter 115 of the dilution opening 68. The outer wall 114 extends from the cold surface side 57 of the outer liner 54 to the hot surface side 59 of the outer liner 54. Figure 6 The outer wall 114 defines a dilution opening centerline axis 116 that passes through the dilution opening 68. The dilution opening 68 also includes a plurality of swirl vanes 118 extending from the outer wall 114 into a dilution airflow passage 120 that extends through the dilution opening 68. Figure 2 Where the inner or outer liner 52, 54 shown is a single-layer liner, the dilution opening 68 may be formed as a cold slot in which a groove is machined through the liner to form the swirl vanes 118. Alternatively, the dilution opening 68 with the swirl vanes 118 may be formed as a separate grommet that may be inserted into the opening of the liner.

[0036] The outer wall 114 further defines a flow-direction centerline 117 extending between the upstream side 108 of the dilution opening 68 and the downstream side 110 of the dilution opening 68. A first circumferential sector 119 is defined about the outer wall 114 on a first side 144 of the dilution opening 68, and a second circumferential sector 121 is defined about the outer wall 114 on a second side 146 of the dilution opening 68, which is opposite the first side 144 of the dilution opening 68. A plurality of swirl vanes 118 are arranged in a continuous arrangement about the outer wall 114 from the upstream side 108 of the dilution opening 68 to the downstream side 110 of the dilution opening 68. For example, when traversing around the outer wall 114 from the most upstream point 132 to the most downstream point 134 along the first side 144 of the dilution opening 68, the first swirl vane 122 may be arranged at the most upstream point 132, and then, arranged successively along the outer wall 114 are the second swirl vane 124, the third swirl vane 126, the fourth swirl vane 128, the fifth swirl vane 130, the sixth swirl vane 136, the seventh swirl vane 138, the eighth swirl vane 140, and the ninth swirl vane 142. The consecutive arrangement of the second swirl vane 124, the third swirl vane 126, the fourth swirl vane 128, the fifth swirl vane 130, the sixth swirl vane 136, the seventh swirl vane 138, and the eighth swirl vane 140 may be referred to as a first group 125 of swirl vanes. A similar continuous arrangement of swirl vanes 118 may also be included when traversing the outer wall 114 from the most upstream point 132 to the most downstream point 134 on the second side 146 of the dilution opening 68. The continuous arrangement may include a tenth swirl vane 192, an eleventh swirl vane 194, a twelfth swirl vane 196, a thirteenth swirl vane 198, a fourteenth swirl vane 200, a fifteenth swirl vane 202, and a sixteenth swirl vane 204 and may be referred to as the second group 127 of swirl vanes.

[0037] For convenience, the outer wall 114 is shown as a cylindrical outer wall 131 defining a dilution hole having a circular cross-section. However, the dilution hole may have any desired cross-sectional shape and is not necessarily limited to a circular shape.

[0038] Each of the plurality of swirl vanes 118 extends from the outer wall 114 into the dilution airflow passage 120 at a corresponding swirl vane angle relative to the outer wall 114, and successive corresponding swirl vanes in the plurality of swirl vanes 118 extend from the outer wall 114 at different swirl vane angles. The swirl vane angle of each corresponding swirl vane can be taken relative to a line extending from the center of the swirl vane 118 at the outer wall 114 to a radial line, the line extending from the center of the swirl vane 118 at the outer wall 114, the radial line emanating from the dilution opening centerline axis 116 and intersecting the outer wall 114 at the same location as the centerline of the swirl vane 118. For example, the first swirl vane 122 can be arranged to extend from the outer wall 114 centered at the most upstream point 132. A first line 148 extending from the most upstream point 132 to the dilution opening centerline axis 116 is generally parallel to the flow direction 85. The first swirl vane 122 extends from the outer wall 114 at a first swirl vane angle 123 . The first swirl vane 122 may be substantially perpendicular to the outer wall 114 , thus having a first swirl vane angle 123 of zero degrees relative to the first line 148 .

[0039] The next consecutive swirl vane (the second swirl vane 124) is arranged on a second line 150 extending between the dilution opening centerline axis 116 and a second point 154 on the outer wall 114, wherein the second line 150 is angularly offset from the first line 148 by an angle 152. As an example, the angle 152 may be 22.5 degrees. However, unlike the first swirl vane 122, which extends perpendicularly from the outer wall 114, the second swirl vane 124 extends from the outer wall 114 at a second swirl vane angle 156 relative to the second line 150. The second swirl vane angle 156 of the second swirl vane 124 may be, for example, 15 degrees. The next consecutive swirl vane (the third swirl vane 126) is arranged on a third line 158 extending between the dilution opening centerline axis 116 and a third point 162 on the outer wall 114, wherein the third line 158 is angularly offset from the second line 150 by an angle 160. As an example, angle 160 may be 22.5 degrees. The third swirl vane 126 extends from the outer wall 114 at a third swirl vane angle 164 relative to the third line 158. The third swirl vane angle 164 of the third swirl vane 126 may be, for example, 30 degrees. Of course, the first swirl vane angle 123, the second swirl angle 156, and the third swirl vane angle 164 are not limited to the above-described exemplary angles and may alternatively be arranged at other angles. The specific angle selected may be based on, for example, the desired amount of swirl or direction of the swirl of the dilution air 82(c), or the circumferential position of the swirl vanes along the outer wall 114.

[0040] Each of the remaining swirl vanes 118 may include lines similar to the first line 148, the second line 150, and the third line 158, and each corresponding line may be spaced 22.5 degrees apart from the previous line, similar to angles 152 and 160. Each corresponding swirl vane 118 is arranged at its own corresponding swirl vane angle. Thus, for example, the fourth swirl vane 128 is arranged at a fourth swirl vane angle 166 relative to the fourth line 168, where the fourth swirl vane angle 166 may be, for example, 40 degrees. The fifth swirl vane 130 may be arranged at a fifth swirl vane angle 170 relative to the fifth line 172, where the fifth swirl vane angle 170 may be, for example, 45 degrees. The sixth swirl vane 136 may be arranged at a sixth swirl vane angle 174 relative to the sixth line 176, where the sixth swirl vane angle 174 may be, for example, 60 degrees. The seventh swirl vane 138 can be arranged at a seventh swirl vane angle 178 relative to a seventh line 180, wherein the seventh swirl vane angle 178 can be, for example, seventy degrees. The eighth swirl vane 140 can be arranged at an eighth swirl vane angle 182 relative to an eighth line 184, wherein the eighth swirl vane angle 182 can be, for example, fifteen degrees. The ninth swirl vane 142 can be arranged at a ninth swirl vane angle 188 relative to a ninth line 186, wherein the ninth swirl vane angle 188 can be, for example, zero degrees, such that the ninth swirl vane 142 extends perpendicularly from the outer wall 114 into the dilution air flow passage 120. Thus, each successive swirl vane 118 in the first set 125 of swirl vanes, from the second swirl vane 124 to the eighth swirl vane 140, is arranged at a different swirl vane angle to induce preferential swirl in the dilution air 82(c) flow as it passes through the dilution opening 68. Utilizing the aforementioned exemplary swirl vane angles, the first set 125 of swirl vanes is configured to induce preferential swirl of the dilution air 82(c) passing through the dilution openings 68 in a first swirl direction 190 (i.e., a clockwise flow direction). The first swirl direction 190 may also be referred to as a dilution opening swirl direction. Figure 3 , the dilution opening swirl direction 190 on the downstream side 110 of the dilution opening 68 may be in the same swirl direction as the mixer swirl direction 63 .

[0041] The plurality of swirl vanes 118 in the second group 127 of swirl vanes arranged along the second side 146 of the dilution opening 68 may be arranged as mirror images of the swirl vanes 118 on the first side 144 of the dilution opening 68 across the flow-direction centerline 117. For example, the tenth swirl vane 192 may be a mirror image of the second swirl vane 124, the eleventh swirl vane 194 may be a mirror image of the third swirl vane 126, the twelfth swirl vane 196 may be a mirror image of the fourth swirl vane 128, the thirteenth swirl vane 198 may be a mirror image of the fifth swirl vane 130, the fourteenth swirl vane 200 may be a mirror image of the sixth swirl vane 136, the fifteenth swirl vane 202 may be a mirror image of the seventh swirl vane 138, and the sixteenth swirl vane 204 may be a mirror image of the eighth swirl vane 140. Thus, in the mirror-image arrangement of the second set 127 of swirl vanes 118 along the second side 146 of the dilution openings 68, the swirl vanes 118 are arranged at different swirl vane angles to induce preferential swirl of the dilution air 82(c) passing through the dilution openings 68 in a second swirl direction 206 that is opposite to the first swirl direction 190. Of course, the plurality of swirl vanes 118 in the second set 127 of swirl vanes may be arranged to induce preferential swirl of the dilution air 82(c) passing through the dilution openings 68 in the same direction (i.e., in the first swirl direction 190) as the plurality of swirl vanes 118 in the first set 125 of swirl vanes.

[0042] Figure 6 According to aspects of the present disclosure Figure 5 A view of the outer wall 114 and the swirl vane 118 taken at view BB in FIG. Figure 6 , the plurality of swirl vanes 118 are shown extending along a length 208 of the outer wall 114 from the cold surface side 57 to the hot surface side 59. It can also be seen that the plurality of swirl vanes 118 extend at an angle 211 between the cold surface side 57 and the hot surface side 59. Figure 6 The swirl vanes 118 may be depicted as being generally linearly angled from the cold surface side 57 to the hot surface side 59 , but the swirl vanes 118 may alternatively be formed as helical vanes extending along the outer wall 114 .

[0043] Figure 7 According to another aspect of the present disclosure Figure 5 BB in FIG, , shows an outer wall 114 and swirl vanes 118 that may extend partially along a length 208 of the outer wall 114 between the cold surface side 57 and the hot surface side 59. For example, the plurality of swirl vanes 118 may have a length 210 that extends partially along a length 210 of the outer wall 114 from the cold surface side 57 toward the hot surface side 59.

[0044] Likewise Figure 7As shown, the swirl vanes 118 may each have a thickness 212, and the thickness 212 of each swirl vane may be the same. Alternatively, as shown Figure 8 As shown, Figure 8 Also in Figure 5 BB in FIG. 1 shows an illustration of the outer wall 114 and swirl vanes 118. The swirl vanes 118 may have different thicknesses. For example, the fifth swirl vane 130 may have a first thickness 214, while the sixth swirl vane 136 may have a second thickness 216 that is less than the first thickness 214. Furthermore, the thickness of the swirl vanes 118 may vary along the length of the swirl vanes 118. For example, the second swirl vane 124 may have a first thickness 218 closest to the cold surface side 57 and a second thickness 220 closest to the hot surface side 59, wherein the first thickness 218 is greater than the second thickness 220. The thickness of the second swirl vane 124 may include a continuous transition between the first thickness 218 and the second thickness 220 along the length 210 of the second swirl vane 124. Of course, a thickness that varies along the length of the swirl vane 118 may be implemented for each swirl vane 118, or may be implemented for only some of the swirl vanes 118.

[0045] In the foregoing description, each swirl vane 118 is described as having a constant swirl vane angle along the length of the swirl vane 118. That is, for example, for the fifth swirl vane 130, the fifth swirl vane angle 170 ( Figure 5 ) are the same along the length 208 of the swirl vane 118. Figures 9 to 11 , a swirl vane 118 having a varying swirl vane angle along the length 208 of the swirl vane 118 will now be provided. Figure 9 is Figure 7 A partial cross-sectional view through the fifth swirl vane 130 taken at plane 9-9, which is closest to the cold surface side end 223 of the fifth swirl vane 130. Figure 9 In the cross section of FIG, the fifth swirl vane 130 is arranged at a fifth swirl vane angle 170, which may be forty-five degrees. Figure 10 is Figure 7 The partial cross-sectional view is taken at plane 10-10 of FIG. 1 , which is near the midpoint along the length 208 of the fifth swirl vane 130. Figure 10 , the fifth swirl vane 130 is shown arranged at a swirl vane angle 222, which may be, for example, thirty-five degrees. The fifth swirl vane 130 includes a constant transition between the fifth swirl vane angle 170 and the swirl vane angle 222 along the length 208 of the fifth swirl vane 130 between plane 9-9 and plane 10-10. Figure 11 is Figure 7FIG2 is a partial cross-sectional view taken at plane 11-11 of FIG2 , which is closest to the hot surface side end 226 of the fifth swirl vane 130. At plane 11-11, the fifth swirl vane 130 is shown arranged at a swirl vane angle 224, which may be, for example, twenty-five degrees. The swirl vane 130 has a constant transition from swirl vane angle 222 to swirl vane angle 224 along the length 208 of the fifth swirl vane 130 between planes 10-10 and 11-11. Thus, the fifth swirl vane 130 transitions from swirl vane angle 170 (forty-five degrees) at the cold surface side end 223 to swirl vane angle 224 (twenty-five degrees) at the hot surface side end 226. Any one or more of the swirl vanes 118 may include a varying swirl vane angle along the length 208 of the swirl vane 118.

[0046] Figure 12 According to another aspect of the present disclosure, Figure 5 An alternative to the enlarged view of the dilution opening 68 shown in FIG. Figure 5 In a similar manner to the aspects of FIG, the outer wall 114 defines a flow direction centerline 117 extending between the upstream side 108 of the dilution opening 68 and the downstream side 110 of the dilution opening 68. Figure 12 In an aspect of the present invention, multiple sectors may be defined around the circumference of the outer wall 114. For example, four sectors may be defined by a first line 228 and a second line 230. The first line 228 extends through the dilution opening 68 between a first point 232 on the upstream side 108 of the outer wall 114 and a second point 234 on the downstream side 110 of the outer wall 114. The second line 230 extends through the dilution opening 68 between a third point 236 on the upstream side 108 of the outer wall 114 and a fourth point 238 on the downstream side 110 of the outer wall 114. The first line 228 may be offset clockwise from the flow direction centerline 117 relative to the dilution opening centerline axis 116 by an angle 240, which may be, for example, fifteen degrees. Similarly, the second line 230 may be offset counterclockwise from the flow direction centerline 117 by an angle 242 relative to the dilution opening centerline axis 116, which may be, for example, fifteen degrees. The first line 228 and the second line 230 define a first sector 244 that extends along the upstream side 108 of the dilution opening 68 between the first point 232 and the third point 236; a second sector 246 that is opposite the first sector 244 and extends along the downstream side 110 of the dilution opening 68 between the second point 234 and the fourth point 238; a third sector 248 that extends between the first sector 244 and the second sector 246 on the first side 144 of the dilution opening 68; and a fourth sector 250 that is opposite the third sector 248 and extends between the first sector 244 and the second sector 246 on the second side 146 of the dilution opening 68.

[0047] exist Figure 12 , the first sector 244 is shown without the plurality of swirl vanes 118. For example, Figure 5 Compared with Figure 12 In the aspect of FIG, the upstream side 108 is devoid of the first swirl vane 122, the second swirl vane 124, and the tenth swirl vane 192. Similarly, the second sector 246 is shown devoid of the plurality of swirl vanes 118. For example, in FIG. Figure 12 The downstream side 110 in the embodiment of the present invention is devoid of the eighth swirl vane 140, the ninth swirl vane 142, and the sixteenth swirl vane 204. By omitting the plurality of swirl vanes 118 on both the upstream side 108 and the downstream side 110, better penetration of the dilution air 82(c) into the dilution zone 75 of the combustion chamber 62 may be achieved.

[0048] On the other hand, a first group 252 of swirl vanes is arranged in the third sector 248, and a second group 254 of swirl vanes is arranged in the fourth sector 250. For example, the first group 252 of swirl vanes may include the third swirl vane 126, the fourth swirl vane 128, the fifth swirl vane 130, the sixth swirl vane 136, and the seventh swirl vane 138. The first group 252 of swirl vanes may be configured to induce swirl in the dilution air 82(c) about the dilution opening centerline axis 116 in the first swirl direction 190. Similarly, the second group 254 of swirl vanes may include the eleventh swirl vane 194, the twelfth swirl vane 196, the thirteenth swirl vane 198, the fourteenth swirl vane 200, and the fifteenth swirl vane 202. The second set of swirl vanes 254 may be configured to induce swirl in the dilution air 82(c) about the dilution opening centerline axis 116 in a second swirl direction 206 that is opposite to the first swirl direction 190. Of course, the second set of swirl vanes 254 may be configured to induce swirl in the dilution air 82(c) about the dilution opening centerline axis 116 in the first swirl direction 190 (i.e., in the same swirl direction as the first set of swirl vanes 252).

[0049] Figure 13 According to another aspect of the present disclosure Figure 5 Another alternative is an enlarged view of the dilution opening 68. Figure 13 In aspects of the present invention, multiple sectors can be defined around the circumference of the outer wall 114. For example, two sectors can be defined by a line 256 that is generally orthogonal to the flow direction centerline 117 and extends between a first point 258 on the outer wall 114 and a second point 260 on the outer wall 114. The first sector 262 generally corresponds to the upstream half of the outer wall 114, and the second sector 264 generally corresponds to the downstream half of the outer wall 114. Figure 12 In an aspect of the present invention, the first sector 262 may be free of swirl vanes 118, while the second sector 264 may include a plurality of swirl vanes 118. Figure 5 Similarly, each swirl vane 118 is arranged at a different respective swirl vane angle. For example, the first swirl vane 266 may be arranged at a first swirl vane angle 268, the second swirl vane 270 may be arranged at a second swirl vane angle 272, the third swirl vane 274 may be arranged at a third swirl vane angle 276, the fourth swirl vane 278 may be arranged at a fourth swirl vane angle 280, the fifth swirl vane 282 may be arranged at a fifth swirl vane angle 284, the sixth swirl vane 286 may be arranged at a sixth swirl vane angle 290, the seventh swirl vane 292 may be arranged at a seventh swirl vane angle 294, the eighth swirl vane 296 may be arranged at an eighth swirl vane angle 298, and the ninth swirl vane 300 may be arranged at a ninth swirl vane angle 302. Figure 13 In the aspect of the present invention, the plurality of swirl vanes 118 are arranged to induce swirl in the dilution air 82(c) in a first swirl direction 190 about the dilution opening centerline axis 116. Thus, without the swirl vanes 118 in the first sector 262 on the upstream half of the dilution opening 68, maximum penetration of the dilution air 82(c) into the dilution zone 75 of the combustion chamber 62 can be achieved, while the swirl of the dilution air 82(c) induced by the swirl vanes 118 in the second sector 264 can fill the wake region that would otherwise be present on the downstream side 110 at the hot surface side 59 of the outer liner 54.

[0050] The foregoing description includes examples of specific swirl vane angles for each of a plurality of swirl vanes, e.g. Figure 5 The above examples of swirl vane angles are provided for a first swirl vane angle 123 (zero degrees), a second swirl vane angle 156 (fifteen degrees), a third swirl vane angle 164 (thirty degrees), and so on. However, the specific swirl vane angles are not limited to the above exemplary angles and may be other angles instead. The specific angle selected may be based on, for example, the desired amount of swirl or direction of swirl of the dilution air 82(c), or the circumferential position of the swirl vanes along the outer wall 114. As a general example of a range of swirl vane angles for swirl vanes, refer to Figure 12 The swirl vanes 118 in the four sectors, including the third sector 248, may be arranged to have a swirl vane angle in the range of thirty to seventy degrees, and the swirl vanes 118 in the fourth sector 250 may be arranged to have a swirl vane angle in the range of negative thirty to negative seventy degrees. In addition, although the first sector 244 and the second sector 246 are shown without swirl vanes, Figure 5The first swirl vane 122, the second swirl vane 124, and the tenth swirl vane 192 shown in FIG may be included within the first sector 244, and the swirl vanes 118 included within the first sector 244 may have a swirl vane angle in the range from zero degrees to thirty degrees along a portion of the first sector 244 that extends from the flow direction centerline 117 to the first point 232, and may have a swirl vane angle in the range from zero degrees to negative thirty degrees over a portion of the first sector 244 that extends from the flow direction centerline 117 to the third point 236. Similarly, the second sector 246 may include the eighth swirl vane 140, the ninth swirl vane 142, and the sixteenth swirl vane 204, and the swirl vanes 118 included in the second sector 246 may have a swirl vane angle in the range from zero degrees to thirty degrees along a portion of the second sector 246 that extends from the flow-direction centerline 117 to the fourth point 238, and may have a swirl vane angle in the range from zero degrees to negative thirty degrees over a portion of the second sector 246 that extends from the flow-direction centerline 117 to the second point 234.

[0051] Each of the above-described aspects of the dilution openings 68 has been described with respect to the dilution openings 68 being integral with the outer liner 54. However, the plurality of dilution openings 68 and the plurality of dilution openings 69 may be implemented within an insert or grommet that may be mounted within the outer liner 54 or the inner liner 52. Furthermore, while a single-layer outer liner 54 has been described above, the dilution openings 68 may also be implemented within a multi-layer liner. Figures 14 to 16 Depicted in Figure 2 An example of a detailed view 304 of FIG, wherein the dilution opening 68 may be implemented as a grommet in a multi-layer liner. Figure 14 , the outer liner 54 is shown to include an outer shell 306 and an inner tile 308, which can be connected together by a connector 309 (such as a bolt connection) to define a cavity 310 therebetween. The dilution opening 68 is implemented as a grommet 312, which can be inserted through an outer shell opening 314 in the outer shell 306 and passed through an inner tile opening 316 of the inner tile 308. The outer shell 306 includes an outer shell cold surface side 318, and the inner tile 308 includes an inner tile hot surface side 320, and the grommet 312 can be arranged to extend from the outer shell cold surface side 318 to the inner tile hot surface side 320. Figure 15 In an alternative arrangement of the grommet 312 shown, the grommet 312 may be arranged to extend a height 322 from the housing cold surface side 318 into the outer flow passage 88. Figure 16In another example shown, the grommet 312 can be integrally formed with the inner shoe 308 and can include a shoulder 324 that can act as a spacer between the outer shell 306 and the inner shoe 308. Of course, the grommet 312 can alternatively be integrally formed with the outer shell 306.

[0052] Furthermore, while the dilution openings 68 have been described herein as extending from the cold surface side 57 of the outer liner 54 to the hot surface side 59 of the outer liner 54 , when the dilution openings 68 are implemented via an insert, the insert may extend beyond the cold surface side 57 of the outer liner 54 into the outer flow passage 88 or may extend beyond the hot surface side 59 of the outer liner 54 into the dilution zone 75 of the combustion chamber 62 .

[0053] While the foregoing description generally relates to gas turbine engines, it will be readily understood that gas turbine engines may be implemented in a variety of environments. For example, the engine may be implemented in an aircraft, but may also be implemented in non-aircraft applications such as power plants, marine applications, or oil and gas production applications. Therefore, the present disclosure is not limited to use in aircraft.

[0054] Further aspects of the disclosure are provided by the subject matter of the following clauses.

[0055] A combustor liner for a gas turbine, the combustor liner comprising: a liner at least partially defining a combustion chamber, wherein the liner includes a plurality of dilution openings therethrough, each of the plurality of dilution openings being defined by (a) an outer wall and (b) a plurality of swirl vanes, the outer wall defining an outer periphery of the dilution openings and defining a dilution opening centerline axis passing through the dilution openings, the plurality of swirl vanes extending from the outer wall into a dilution airflow passage, the dilution airflow passage extending through the dilution openings, each of the plurality of swirl vanes extending from the outer wall into the dilution airflow passage at a respective swirl vane angle relative to the outer wall, the plurality of swirl vanes being arranged in a continuous arrangement about the outer wall, and consecutive respective ones of the plurality of swirl vanes extending from the outer wall at different swirl vane angles.

[0056] The combustor liner of the preceding clause, wherein the liner includes an inner liner and an outer liner, the inner liner and outer liner each extending circumferentially about a combustor centerline axis and extending in a longitudinal direction along the combustor centerline axis, the plurality of dilution openings being circumferentially spaced from one another about the inner liner and about the outer liner.

[0057] The combustor liner of any preceding clause, wherein the plurality of dilution openings includes a first group of dilution openings arranged circumferentially along the combustor centerline axis at a first longitudinal position, and a second group of dilution openings arranged circumferentially along the combustor centerline axis at a second longitudinal position.

[0058] The combustor liner of any preceding clause, wherein the liner includes a cold surface side adjacent to the outer flow passage and a hot surface side adjacent to the combustion chamber, each dilution opening extending from the cold surface side to the hot surface side.

[0059] The combustor liner of any preceding clause, wherein the plurality of swirl vanes extend along a length of the outer wall from the cold surface side to the hot surface side.

[0060] The combustor liner of any preceding clause, wherein the plurality of swirl vanes extend along a length of the outer wall between the cold surface side and the hot surface side, and respective swirl vanes of the plurality of swirl vanes define a varying swirl vane angle along the length of the swirl vane, the varying swirl vane angle being a first swirl vane angle at the cold surface side of the swirl vane and a second swirl vane angle at the hot surface side of the swirl vane, the second swirl vane angle being different from the first swirl vane angle.

[0061] The combustor liner of any preceding clause, wherein the plurality of swirl vanes extend partially along the length of the outer wall between the cold surface side and the hot surface side.

[0062] The combustor liner of any preceding clause, wherein the plurality of swirl vanes extend from the cold surface side partially along the length of the outer wall toward the hot surface side.

[0063] The combustor liner of any preceding clause, wherein the outer wall is a cylindrical wall extending from the cold surface side to the hot surface side, and the plurality of swirl vanes extend from the cylindrical wall into the dilution airflow channel.

[0064] The combustor liner of any preceding clause, wherein the outer wall defines a flow direction centerline extending between an upstream side of the dilution opening and a downstream side of the dilution opening, a first sector is defined about the outer wall on a first side of the dilution opening, and a second sector is defined about the outer wall on a second side of the dilution opening, the second side of the dilution opening being opposite the first side of the dilution opening, a first group of swirl vanes of the plurality of swirl vanes being arranged in the first sector and configured to induce swirl of air in a first swirl direction about the dilution opening centerline axis, and a second group of swirl vanes of the plurality of swirl vanes being arranged in the second sector and configured to induce swirl of air in a second swirl direction about the dilution opening centerline axis.

[0065] The combustor liner of any preceding clause, wherein the first swirl direction and the second swirl direction are the same swirl direction.

[0066] The combustor liner of any preceding clause, wherein the first swirl direction and the second swirl direction are opposite swirl directions.

[0067] The combustor liner of any preceding clause, wherein the outer wall defines a flow direction centerline extending between an upstream side of the dilution opening and a downstream side of the dilution opening, the plurality of sectors defined around the periphery of the outer wall including a first sector extending along the upstream side of the dilution opening, a second sector extending along the downstream side of the dilution opening, a third sector extending between the first and second sectors on a first side of the dilution opening, and a fourth sector extending between the first and second sectors on a second side of the dilution opening, the second sector being opposite the first sector, and the fourth sector being opposite the third sector.

[0068] The combustor liner of any preceding clause, wherein the first and second sectors are devoid of the plurality of swirl vanes, and the plurality of swirl vanes are included in the third and fourth sectors.

[0069] The combustor liner of any preceding clause, wherein the plurality of swirl vanes includes a first group of swirl vanes arranged in the third sector and a second group of swirl vanes arranged in the fourth sector, the first group of swirl vanes configured to induce swirl of the dilution air about the dilution opening centerline axis in a first swirl direction, and the second group of swirl vanes configured to induce swirl of the dilution air about the dilution opening centerline axis in a second swirl direction.

[0070] The combustor liner of any preceding clause, wherein the first swirl direction and the second swirl direction are the same direction about the dilution opening centerline axis.

[0071] The combustor liner of any preceding clause, wherein the first swirl direction and the second swirl direction are opposite directions about the dilution opening centerline axis.

[0072] A combustor liner according to any preceding clause, wherein, in a plan view of the cold surface side of the liner, the dilution opening swirl direction along the downstream side of the dilution opening is the same swirl direction as a mixer swirl direction of a mixer assembly about a mixer assembly centerline axis extending longitudinally through the combustion chamber.

[0073] The combustor liner of any preceding clause, wherein the plurality of swirl vanes extend partially along the length of the outer wall between the cold surface side and the hot surface side, and wherein the plurality of swirl vanes include a thickness that varies along the length of the swirl vanes.

[0074] The combustor liner of any preceding clause, wherein a respective swirl vane of the plurality of swirl vanes has a first thickness on a cold surface side of the swirl vane and a second thickness on a hot surface side of the swirl vane, the second thickness being different from the first thickness.

[0075] Although the foregoing description is directed to some exemplary embodiments of the present disclosure, other variations and modifications will be apparent to those skilled in the art and may be made without departing from the spirit or scope of the present disclosure. In addition, the features described in conjunction with one embodiment of the present disclosure may be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A combustor liner for a gas turbine, characterized in that The combustor liner comprises: a liner at least partially defining a combustion chamber, wherein the liner includes a plurality of dilution openings therethrough, each of the plurality of dilution openings being defined by (a) an outer wall and (b) a plurality of swirl vanes, the outer wall defining an outer periphery of the dilution opening and defining a dilution opening centerline axis passing through the dilution opening, the plurality of swirl vanes extending from the outer wall into a dilution airflow passage, the dilution airflow passage extending through the dilution opening, each of the plurality of swirl vanes extending from the outer wall into the dilution airflow passage at a respective swirl vane angle relative to the outer wall, the plurality of swirl vanes being arranged in a continuous arrangement about the outer wall, and consecutive respective ones of the plurality of swirl vanes extending from the outer wall at different swirl vane angles.

2. The combustor liner according to claim 1, wherein: in, The liner includes an inner liner and an outer liner each extending circumferentially about a combustor centerline axis and extending in a longitudinal direction along the combustor centerline axis, the plurality of dilution openings being circumferentially spaced apart from one another about the inner liner and about the outer liner.

3. The combustor liner according to claim 2, wherein: in, The plurality of dilution openings includes a first group of dilution openings arranged circumferentially along the combustor centerline axis at a first longitudinal position, and a second group of dilution openings arranged circumferentially along the combustor centerline axis at a second longitudinal position.

4. The combustor liner according to claim 1, wherein: in, The liner includes a cold surface side adjacent to the outer flow passage and a hot surface side adjacent to the combustion chamber, each dilution opening extending from the cold surface side to the hot surface side.

5. The combustor liner according to claim 4, characterized in that in, The plurality of swirl vanes extend along a length of the outer wall from the cold surface side to the hot surface side.

6. The combustor liner according to claim 4, wherein: in, The plurality of swirl vanes extend along a length of the outer wall between the cold surface side and the hot surface side, and respective swirl vanes of the plurality of swirl vanes define a varying swirl vane angle along the length of the swirl vane, the varying swirl vane angle being a first swirl vane angle at the cold surface side of the swirl vane and a second swirl vane angle at the hot surface side of the swirl vane, the second swirl vane angle being different from the first swirl vane angle.

7. The combustor liner according to claim 4, wherein: in, The plurality of swirl vanes extend partially along a length of the outer wall between the cold surface side and the hot surface side.

8. The combustor liner according to claim 7, wherein: in, The plurality of swirl vanes extend from the cold surface side partially along the length of the outer wall toward the hot surface side.

9. The combustor liner according to claim 4, wherein: in, The outer wall is a cylindrical wall extending from the cold surface side to the hot surface side, and the plurality of swirl vanes extend from the cylindrical wall into the dilution airflow channel.

10. The combustor liner according to claim 1, wherein: in, The outer wall defines a flow direction centerline extending between an upstream side of the dilution opening and a downstream side of the dilution opening, a first sector is defined around the outer wall on a first side of the dilution opening, and a second sector is defined around the outer wall on a second side of the dilution opening, the second side of the dilution opening being opposite the first side of the dilution opening, a first group of swirl vanes among the plurality of swirl vanes being arranged in the first sector and configured to induce swirl of air in a first swirl direction about the dilution opening centerline axis, and a second group of swirl vanes among the plurality of swirl vanes being arranged in the second sector and configured to induce swirl of air in a second swirl direction about the dilution opening centerline axis.

11. The combustor liner according to claim 10, wherein: in, The first swirl direction and the second swirl direction are the same swirl direction.

12. The combustor liner according to claim 10, wherein: in, The first swirl direction and the second swirl direction are opposite swirl directions.

13. The combustor liner according to claim 1, wherein: in, The outer wall defines a flow direction centerline extending between an upstream side of the dilution opening and a downstream side of the dilution opening, and a plurality of sectors defined around the outer circumference of the outer wall include a first sector extending along the upstream side of the dilution opening, a second sector extending along the downstream side of the dilution opening, a third sector extending between the first sector and the second sector on the first side of the dilution opening, and a fourth sector extending between the first sector and the second sector on the second side of the dilution opening, the second sector being opposite to the first sector, and the fourth sector being opposite to the third sector.

14. The combustor liner according to claim 13, wherein: in, The first and second sectors are devoid of the plurality of swirl vanes, and the plurality of swirl vanes are included in the third and fourth sectors.

15. The combustor liner according to claim 14, wherein: in, The plurality of swirl vanes include a first group of swirl vanes arranged in the third sector and a second group of swirl vanes arranged in the fourth sector, the first group of swirl vanes being configured to induce swirl of the dilution air about the dilution opening centerline axis in a first swirl direction, and the second group of swirl vanes being configured to induce swirl of the dilution air about the dilution opening centerline axis in a second swirl direction.

16. The combustor liner according to claim 15, wherein: in, The first swirl direction and the second swirl direction are the same direction around the centerline axis of the dilution opening.

17. The combustor liner according to claim 15, wherein: in, The first swirl direction and the second swirl direction are opposite directions about the centerline axis of the dilution opening.

18. The combustor liner according to claim 16, wherein: in, In a plan view of the cold surface side of the liner, the dilution opening swirl direction along the downstream side of the dilution opening is the same swirl direction as a mixer swirl direction of a mixer assembly about a mixer assembly centerline axis extending longitudinally through the combustion chamber.

19. The combustor liner according to claim 4, wherein: in, The plurality of swirl vanes extend partially along a length of the outer wall between the cold surface side and the hot surface side, and the plurality of swirl vanes include a thickness that varies along the length of the swirl vanes.

20. The combustor liner according to claim 19, wherein in, A corresponding swirl vane of the plurality of swirl vanes has a first thickness on a cold surface side of the swirl vane and a second thickness on a hot surface side of the swirl vane, the second thickness being different from the first thickness.

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