Annular combustor dilution with swirl vanes for reduced emissions

Abstract

A combustor liner for a combustor of a gas turbine includes an outer liner and an inner liner. The outer liner has an annular outer liner slot dilution opening, and a plurality of outer liner swirl vanes are disposed within the annular outer liner slot dilution opening. The inner liner of the combustor liner includes an annular inner liner slot dilution opening, and further includes a plurality of inner liner swirl vanes disposed within the annular inner liner slot dilution opening.

Description

Technical Field

[0001] This disclosure relates to the dilution of combustion gases in the combustion chamber of a gas turbine engine. Background Technology

[0002] In conventional gas turbine engines, it is known to provide a dilution airflow to the combustion chamber downstream of the main combustion zone. Conventionally, an annular combustor bushing may include both an inner bushing and an outer bushing that form the combustion chamber between them. The inner and outer bushings may include dilution orifices through the bushings, providing airflow (i.e., a dilution jet) from a passage around the annular combustor bushing into the combustion chamber. Some applications are known to use circular orifices to provide a dilution airflow to the combustion chamber. The airflow through the circular dilution orifices in a conventional combustor mixes with the combustion gases within the combustion chamber to provide quenching of the combustion gases. The high-temperature region seen behind the dilution jet (i.e., the wake region of the dilution jet) is associated with high NOx formation. Furthermore, the circular dilution air jet does not diffuse laterally, thus generating high temperatures between the dilution jets, which also contributes to high NOx formation. Attached Figure Description

[0003] Features and advantages of this disclosure will become apparent from the following description of various exemplary embodiments, as illustrated in the accompanying drawings, wherein the same reference numerals generally denote the same, functionally similar and / or structurally similar elements.

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

[0005] Figure 2 This is a cross-sectional side view of an exemplary combustion section according to an embodiment of the present disclosure.

[0006] Figure 3 The embodiments of the present disclosure are described in Figure 1 A partial cross-sectional view of the burner bushing taken at plane 3-3.

[0007] Figure 4 A partial cross-sectional side view of an exemplary burner bushing according to one aspect of this disclosure is depicted.

[0008] Figure 5 It is based on one aspect of this disclosure. Figure 4 The detailed view of 120 depicts an exemplary annular outer bushing groove dilution opening / outer bushing swirl impeller arrangement.

[0009] Figure 6 It is based on one aspect of this disclosure. Figure 4 A partial cross-sectional view taken at plane 6-6, passing through the dilution opening 114 of the annular outer bushing groove.

[0010] Figure 7 It is based on one aspect of this disclosure. Figure 4 A partial cross-sectional view taken at plane 7-7, passing through the dilution opening 116 of the annular inner liner groove.

[0011] Figure 8 It is based on one aspect of this disclosure. Figure 6 A close-up view of the outer bushing swirl impeller taken at point 172.

[0012] Figures 9A to 9C An alternative arrangement of the outer bushing swirl impeller blades according to one aspect of this disclosure is depicted.

[0013] Figures 10A to 10C A cross-sectional view through the outer bushing swirl vane is depicted according to one aspect of this disclosure.

[0014] Figure 11 Depicting another aspect of this disclosure Figure 4 A detailed view taken at 200° shows an alternative arrangement of the outer and inner bushing grooves, dilution openings, and swirl impeller blades.

[0015] Figure 12 Depicting another aspect of this disclosure Figure 4 A detailed view taken at 200° shows another arrangement of the outer and inner bushing grooves, dilution openings, and swirl impeller blades.

[0016] Figure 13 Depicting another aspect of this disclosure in Figure 4 A detailed view taken at 200° shows another arrangement of the outer and inner bushing grooves, dilution openings, and swirl impeller blades.

[0017] Figure 14 Depicting another aspect of this disclosure in Figure 4 A detailed view taken at 200° shows another arrangement of the outer and inner bushing grooves, dilution openings, and swirl impeller blades.

[0018] Figure 15 Depicting another aspect of this disclosure in Figure 4 A detailed view taken at 200° shows another arrangement of the outer and inner bushing grooves, dilution openings, and swirl impeller blades.

[0019] Figure 16 Depicting another aspect of this disclosure in Figure 4 A detailed view taken at 200° shows another arrangement of the outer and inner bushing grooves, dilution openings, and swirl impeller blades.

[0020] Figure 17 Depicting another aspect of this disclosure in Figure 4A detailed view taken at 200° shows another arrangement of the outer and inner bushing grooves, dilution openings, and swirl impeller blades.

[0021] Figure 18 Depicting another aspect of this disclosure in Figure 4 A detailed view taken at 200° shows another arrangement of the outer and inner bushing grooves, dilution openings, and swirl impeller blades.

[0022] Figure 19 Depicting another aspect of this disclosure in Figure 4 A detailed view taken at 200° shows another arrangement of the outer and inner bushing grooves, dilution openings, and swirl impeller blades.

[0023] Figure 20 Depicting another aspect of this disclosure in Figure 4 A detailed view taken at 200° shows another arrangement of the outer and inner bushing grooves, dilution openings, and swirl impeller blades.

[0024] Figure 21 Depicting another aspect of this disclosure in Figure 4 A detailed view taken at 200° shows another arrangement of the outer and inner bushing grooves, dilution openings, and swirl impeller blades.

[0025] Figure 22 Depicting another aspect of this disclosure in Figure 4 Another arrangement of the outer bushing and inner bushing groove dilution opening and swirl impeller blades, cut at plane 22-22. Detailed Implementation

[0026] Various embodiments are discussed in detail below. Although specific embodiments are discussed, they are for illustrative purposes only. Those skilled in the art will recognize that other components and constructions can be used without departing from the spirit and scope of this disclosure.

[0027] 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.

[0028] The terms "upstream" and "downstream" refer to the relative directions of fluid flow within a fluid path. For example, "upstream" refers to the direction from which fluid flows, and "downstream" refers to the direction from which fluid flows.

[0029] Various embodiments are discussed in detail below. Although specific embodiments are discussed, they are for illustrative purposes only. Those skilled in the art will recognize that other components and constructions can be used without departing from the spirit and scope of this disclosure.

[0030] In the combustion section of a turbine engine, air flows through an external passage surrounding the burner liner. Air typically flows from the upstream end of the burner liner to the downstream end. Some of the airflow in the external passage is diverted through dilution orifices in the burner liner and enters the combustion chamber as dilution air. One purpose of the dilution airflow is to cool (i.e., quench) the combustion gases in the combustion chamber before they enter the turbine section. However, the combustion products from the primary zone must be quenched quickly and effectively to minimize the high-temperature region and thus reduce NOx emissions from the combustion system.

[0031] This disclosure aims to reduce NOx emissions by improving the dilution and quenching of hot combustion gases from the main combustion zone. According to this disclosure, the burner liner includes an outer liner with an annular outer liner groove dilution opening, and a plurality of outer liner swirl vanes disposed within the annular outer liner groove dilution opening. Similarly, the inner liner of the burner liner includes an annular inner liner groove dilution opening, and also includes a plurality of inner liner swirl vanes disposed within the annular inner liner groove dilution opening. Therefore, the annular groove generally provides a uniform distribution of air entering the combustion chamber from the surrounding flow channels, and the swirl vanes can introduce swirls into the air passing through the groove dilution opening. Thus, the diluted air entering the combustion chamber can achieve better distribution, and better mixing of the diluted air and combustion gases can be achieved via the turbulence provided by the swirling airflow.

[0032] Now refer to the attached diagram, Figure 1 This is a schematic partial cross-sectional side view of an exemplary high-bypass turbofan jet engine 10 (referred to herein as "engine 10"), which may be incorporated into various embodiments of this disclosure. Although further description follows with reference to turbofan engines, this disclosure is generally also applicable to turbomachinery, including turbojet engines, turboprop engines, and turboshaft gas turbine engines, including marine and industrial turbine engines and auxiliary power units. Figure 1 As shown, engine 10 has an axial centerline axis 12, which, for reference purposes, extends from an upstream end 98 to a downstream end 99. Typically, engine 10 may include a fan assembly 14 and a core engine 16 disposed downstream of the fan assembly 14.

[0033] The core engine 16 typically includes a housing 18 defining an annular inlet 20. The housing 18 surrounds or at least partially forms, in a series flow relationship, a compressor section having a supercharger or low-pressure (LP) compressor 22 and a high-pressure (HP) compressor 24, a combustion section 26, a turbine section including a high-pressure (HP) turbine 28 and a low-pressure (LP) turbine 30, and an exhaust nozzle section 32. A high-pressure (HP) rotor shaft 34 drivesly connects the HP turbine 28 to the HP compressor 24. A low-pressure (LP) rotor shaft 36 drivesly 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, such as Figure 1 As shown, the LP rotor shaft 36 can be connected to the fan shaft 38 via a reduction gear 40, for example in an indirect drive configuration or a gear drive configuration. In other embodiments, although not shown, the engine 10 may further include an intermediate pressure (IP) compressor and a turbine that rotates with the intermediate pressure shaft.

[0034] 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 housing or nacelle 44 circumferentially surrounds the fan assembly 14 and / or at least a portion of the core engine 16. In one embodiment, the nacelle 44 may be supported relative to the core engine 16 by a plurality of circumferentially spaced outlet guide vanes or struts 46. Furthermore, at least a portion of the nacelle 44 may extend above the outer portion of the core engine 16 to define a bypass airflow passage 48 therebetween.

[0035] Figure 2 Is it like this? Figure 1 A cross-sectional side view of an exemplary combustion section 26 of the core engine 16 shown. Figure 2 As shown, combustion section 26 typically includes a cowling 60 connected to burner bushing 50 and dome assembly 56. Burner bushing 50 includes an inner bushing 52 and an outer bushing 54. The inner bushing 52, outer bushing 54, and dome assembly 56 together define combustion chamber 62. Combustion chamber 62 may more specifically define various regions, including a primary combustion zone 71, where initial chemical reactions of the fuel-oxidant mixture and / or recirculation of combustion gases 86 can occur before further downstream flow to dilution zone 72, where mixing and / or recirculation of combustion gases 86 and compressed air 82(c) and 82(d) can occur via turbine inlet 68 into HP turbine 28 and LP turbine 30. Figure 1 This occurs before the dome assembly 56 extends radially between the outer bushing 54 and the inner bushing 52, and includes a cyclone assembly 58 attached thereto.

[0036] like Figure 2 As shown, the inner liner 52 can be enclosed within the inner shell 65, while the outer liner 54 can be enclosed within the outer shell 64. An outer flow channel 88 is defined between the outer shell 64 and the outer liner 54, and an inner flow channel 90 is defined between the inner shell 65 and the inner liner 52. As will be described in more detail below, the outer liner 54 includes an annular outer liner groove dilution opening 114 having a plurality of outer liner swirl vanes 115 disposed therein, and may optionally include a second annular outer liner groove dilution opening 118. Similarly, the inner liner 52 includes an annular inner liner groove dilution opening 116 having a plurality of inner liner swirl vanes 117 disposed therein, and may optionally include a second annular inner liner groove dilution opening 119. The annular outer liner groove dilution opening 114 extends circumferentially through the outer liner 54 about the burner centerline 112, and the annular inner liner groove dilution opening extends circumferentially through the inner liner 52 about the burner centerline 112. The annular outer bushing groove dilution opening 114 has a plurality of outer bushing swirl vanes 115 disposed therein, providing a compressed air flow 82(d) through which swirls are generated as the compressed air 82(d) flows into the dilution zone 72 of the combustion chamber 62. An optional second annular outer bushing groove dilution opening 118 can provide a compressed air flow 82(c) that flows radially through which it enters the dilution zone 72 of the combustion chamber 62. The compressed air flows 82(c) and 82(d) can therefore be used to provide quenching of the combustion gases 86 in the dilution zone 72 to cool the combustion gas flow 86 entering the turbine section. A similar flow of compressed air 82(c) is provided through a second annular inner bushing groove dilution opening 119, and a similar flow of compressed air 82(d) is provided through an annular inner bushing groove dilution opening 116 having a plurality of inner bushing swirl vanes 117 therein.

[0037] During the operation of engine 10, such as Figure 1 and Figure 2 As shown, a certain amount of air 73, as schematically indicated by arrows, enters the engine 10 from the upstream end 98 through the relevant inlet 76 of the nacelle 44 and / or fan assembly 14. As this amount of air 73 passes through the fan blades 42, a portion of the air 73, as schematically indicated by arrow 78, is directed or routed to the bypass airflow passage 48, while another portion of the air 80, as schematically indicated by arrows, is directed or routed to the LP compressor 22. The air 80 is gradually compressed as it flows through the LP compressor 22 and the HP compressor 24 towards the combustion section 26. Reference Figure 2As schematically indicated by the arrow, compressed air 82 now flows into the diffuser cavity 84 of the combustion section 26 and pressurizes the diffuser cavity 84. A first portion of the compressed air 82, as schematically indicated by arrow 82(a), flows from the diffuser cavity 84 into the pressure chamber 66, where it is swirled by the cyclone assembly 58 and mixed with fuel supplied by the fuel nozzle assembly 70 to produce a swirling fuel-air mixture 85. This mixture is injected into the combustion chamber 62 in a swirling direction 87, which is either clockwise or counterclockwise around the cyclone assembly's central axis 144, and is then ignited and burned to produce combustion gases 86. Typically, the LP compressor 22 and the HP compressor 24 ( Figure 1 More compressed air than is required for combustion is supplied to the diffuser cavity 84. Therefore, the second portion of compressed air 82(b), as schematically indicated by the arrow, can be used for various purposes other than combustion. For example, as... Figure 2 As shown, compressed air 82(b) can be routed into the outer flow channel 88 and the inner flow channel 90. A portion of the compressed air 82(b) can then be routed through the annular outer bushing groove dilution opening 114 (schematically shown as compressed air 82(d)) and into the dilution zone 72 of the combustion chamber 62 to provide quenching of the combustion gases 86 in the dilution zone 72. The compressed air 82(d) can also provide turbulence to the combustion gas flow 86 to better mix the compressed air 82(d) with the combustion gases 86. Furthermore, when the second annular outer bushing groove dilution opening 118 is included in the outer bushing 54, a portion of the compressed air 82(b) (schematically shown as compressed air 82(c)) can be routed through the second annular outer bushing groove dilution opening 118 into the dilution zone 72 of the combustion chamber 62. A similar flow of compressed air 82(d) from the inner flow passage 90 passes through the annular inner liner groove dilution opening 116, where it is swirled by multiple inner liner swirl vanes 117 and supplied to the dilution zone 72 of the combustion chamber 62. Furthermore, when a second annular inner liner groove dilution opening 119 is provided, compressed air 82(c) can enter the dilution zone 72 of the combustion chamber 62 via its route.

[0038] Return to reference together Figure 1 and Figure 2 The combustion gases 86 generated in combustion chamber 62 flow from combustion section 26 into HP turbine 28, causing HP rotor shaft 34 to rotate, thereby supporting the operation of HP compressor 24. Figure 1 As shown, the combustion gas 86 is then routed through the LP turbine 30, causing the LP rotor shaft 36 to rotate, thereby supporting the operation of the LP compressor 22 and / or the rotation of the fan shaft 38. The combustion gas 86 is then exhausted through the injection exhaust nozzle section 32 of the core engine 16 to provide propulsion at the downstream end 99.

[0039] Figure 3Is Figure 2 A partial cross-sectional view of the burner bushing 50 taken at plane 3-3, as shown. Figure 3 As shown, the burner bushing 50 is a generally annular bushing extending circumferentially around the centerline axis 12 of the engine 10. Because it may be associated with the burner bushing 50, the centerline axis 12 may also correspond to the burner centerline 112. The burner bushing 50 includes an outer bushing 54 and an inner bushing 52. Representative swirler assemblies 58(a) and 58(b) are shown circumferentially spaced around the burner centerline 112. For each swirler assembly 58(a) and 58(b), a portion of the burner bushing 50 can be considered as a segment of the burner bushing 50. That is, while the burner bushing 50 may be a single, integral bushing extending circumferentially along the burner centerline 112, it can be considered to comprise multiple segments circumferentially around the burner centerline 112 (e.g., a first segment 129, a second segment 131, etc.), each segment corresponding to a respective swirler assembly 58. For example, the first segment 129 may correspond to the first segment cyclone assembly 58(a) and may be defined between segment boundary lines 134 and 136, extending radially outward from the burner centerline 112 and may be aligned with the segment cyclone assembly centerline axis 144 of the first segment cyclone assembly 58(a) (see also...). Figure 2 The segments are spaced apart at equal angles. Similarly, the second segment 131 may be associated with the second segment hydrocyclone assembly 58(b) and may be defined between segment boundary lines 134 and 138. The second segment 131 is adjacent to the first segment 129. The first segment 129 includes a first segment outer bushing 130 and a first segment inner bushing 140, while the second segment 131 includes a second segment outer bushing 132 and a second segment inner bushing 142.

[0040] Figure 4 A partial cross-sectional view of a burner bushing 50 according to one aspect of this disclosure is depicted. Figure 4 The depiction of the first hydrocyclone assembly 58(a) is for reference only. Figure 4 As shown, the burner bushing 50 defines an axial direction (L) parallel to the burner centerline 112, a radial direction (R) extending substantially perpendicular to the burner centerline 112, and a circumferential direction (C) extending around the burner centerline 112. The outer bushing 54 extends circumferentially around the burner centerline 112 and axially from an upstream end 100 to a downstream end 102. An outer bushing dilution zone 108 is defined between the upstream end 100 and the downstream end 102. The outer bushing 54 has a cold surface side 122 adjacent to the outer flow channel 88 and a hot surface side 124 adjacent to the combustion chamber 62. Figure 2As shown and described, a portion of the compressed air 82(b) flows in the outer flow passage 88, and the compressed air 82(b) flows from the upstream end 100 of the outer bushing to the downstream end 102 of the outer bushing, thereby defining an outer flow direction 92 extending in the axial direction (L). The outer bushing 54 further includes an annular outer bushing groove dilution opening 114 in which a plurality of outer bushing swirl vanes 115 are disposed, and optionally, a second annular outer bushing groove dilution opening 118 may be included. The annular outer bushing groove dilution opening 114 and the optional second annular outer bushing groove dilution opening 118 extend generally circumferentially through the outer bushing 54 about the burner centerline 112. As will be described in more detail below, the outer bushing 54 may also include an annular outer bushing radial wall 146, which extends at least partially radially from the outer bushing hot surface side 124 into the combustion chamber 62, wherein a plurality of outer bushing swirl vanes 115 may be disposed on the annular outer bushing radial wall 146. The various arrangements of the annular outer bushing groove dilution opening 114 and the multiple outer bushing swirl vanes 115 will be described in more detail below.

[0041] Figure 4 The burner bushing 50 also includes an inner bushing 52 that extends circumferentially around the burner centerline 112 and extends from an upstream end 104 to a downstream end 106. An inner bushing dilution zone 110 is defined between the upstream end 104 and the downstream end 106. The inner bushing 52 has a cold surface side 126 adjacent to the inner flow passage 90 and a hot surface side 128 adjacent to the combustion chamber 62. Figure 2 As shown and described, a portion of the compressed air 82(b) flows in the inner flow passage 90, and the compressed air 82(b) flows from the upstream end 104 of the inner liner to the downstream end 106 of the inner liner, thereby defining the inner liner flow direction 94 extending in the axial direction (L). The inner liner 52 further includes an annular inner liner groove dilution opening 116 having a plurality of inner liner swirl vanes 117, and optionally, may include a second annular inner liner groove dilution opening 119. As will be described in more detail below, the inner liner 52 may also include an annular inner liner radial wall 148 disposed on the upstream side 149 of the annular inner liner groove dilution opening 116, and which extends at least partially radially from the inner liner hot surface side 128 into the combustion chamber 62, wherein a plurality of inner liner swirl vanes 117 may be disposed on the annular inner liner radial wall 148.

[0042] Figure 5 It is based on one aspect of this disclosure. Figure 4 Detailed view of 120, depicting an exemplary annular outer bushing groove dilution opening / outer bushing swirl impeller arrangement. Figure 5 In, with Figure 4Similarly, the outer bushing 54 includes an annular outer bushing groove dilution opening 114 passing through it, and a plurality of outer bushing swirl vanes 115 are disposed within the annular outer bushing groove dilution opening 114. Figure 5 In this aspect, the annular outer bushing radial wall 146 can be seen disposed on the upstream side 150 of the annular outer bushing groove dilution opening 114. The annular outer bushing radial wall 146 extends circumferentially around the burner centerline 112 and extends at least partially in the radial direction (R) from the outer bushing 54 into the combustion chamber 62. Due to the inclusion of the annular outer bushing radial wall 146, a plurality of outer bushing swirl vanes 115 can be disposed on the downstream side 158 of the annular outer bushing radial wall 146.

[0043] exist Figure 5 In addition, the outer bushing 54 also includes a second annular outer bushing groove dilution opening 118, which is disposed on the upstream side 147 of the radial wall 146 of the annular outer bushing and extends circumferentially through the outer bushing 54 around the burner centerline 112. When implementing the second annular outer bushing groove dilution opening 118, a plurality of bridging members 152 may also be included to bridge gaps in the outer bushing 54. The plurality of bridging members 152 may be circumferentially spaced around the outer bushing 54 and may be brazed or welded to the outer bushing 54. Figure 5 The second annular outer bushing groove dilution opening 118 shown does not include a swirl vane, but as will be described below in conjunction with various additional aspects, a swirl vane may be included in the second annular outer bushing groove dilution opening 118. When the swirl vane is not included in the second annular outer bushing groove dilution opening 118, the compressed air flow 82(c) through it is typically radially guided into the dilution zone 72 of the combustion chamber 62. Figure 4 ) stream.

[0044] Figure 6 Is Figure 4 A partial cross-sectional view taken at plane 6-6 through the dilution opening 114 of the annular outer bushing groove (see also) Figure 5 ).exist Figure 6 In the middle, the cross section can correspond to the first segment 129 between segment boundary line 134 and segment boundary line 136. Figure 3 The first section of the outer bushing is 130. (e.g.) Figure 6 As shown, the annular outer bushing radial wall 146 includes a plurality of outer bushing swirl vanes 115 disposed on the downstream side 158 of the annular outer bushing radial wall 146. The plurality of outer bushing swirl vanes 115 may be spaced apart from each other circumferentially by a circumferential distance 160. The circumferential distance 160 between consecutive outer bushing swirl vanes 115 defines an outer bushing groove dilution opening flow passage 154 between consecutive outer bushing swirl vanes 115. Furthermore, the outer bushing swirl vanes 115 may be arranged at an angle 156 relative to both the radial and circumferential directions. Angle 156 may be based on the compressed air flow 82(d) passing through the annular outer bushing groove dilution opening 114 (…). Figure 4 The required vortex flow rate setting. Figure 6 In the rear-front view of the outer bushing swirl impeller 115, angle 156 is shown such that the outer bushing swirl impeller 115 causes compressed air 82(d) to flow clockwise around the burner centerline 112, which can interact with the swirling fuel-air mixture 85 ( Figure 2 The swirl direction 87 is the same as or opposite to the direction of the airflow. Of course, the angle 156 of the outer bushing swirl impeller 115 can be set to provide compressed air 82(d) around the burner centerline 112(d). Figure 4 The flow is counterclockwise. Although Figure 6 The circumferential distance 160 and angle 156 of each of the plurality of outer bushing swirl blades 115 shown may appear the same, as will be described below, but the angle 156 and circumferential distance 160 between each outer bushing swirl blade 115 may vary.

[0045] Figure 7 Is Figure 4 A partial cross-sectional view taken at plane 7-7, passing through the dilution opening 116 of the annular inner liner groove. Figure 7 In the middle, the cross section can correspond to the first segment 129 between segment boundary line 134 and segment boundary line 136. Figure 3 The first section of the inner liner is 140. (e.g.) Figure 7 As shown, the annular inner bushing radial wall 148 includes a plurality of inner bushing swirl vanes 117 disposed on the downstream side 168 of the annular inner bushing radial wall 148. The plurality of inner bushing swirl vanes 117 are circumferentially spaced apart from each other by a circumferential distance 170. The circumferential distance 170 between consecutive inner bushing swirl vanes 117 defines an inner bushing groove dilution opening flow passage 164 between consecutive inner bushing swirl vanes 117. Furthermore, the inner bushing swirl vanes 117 can be arranged at an angle 166 relative to both the radial and circumferential directions. Angle 166 is based on the compressed air flow 82(d) passing through the annular inner bushing groove dilution opening 116 (…). Figure 4 The required swirl volume is set accordingly. Figure 7 In the rear-front view of the inner bushing swirl impeller 117, angle 166 is shown such that the inner bushing swirl impeller 117 causes compressed air 82(d) to circumferentially travel along the burner centerline 112. Figure 4 ) flows counterclockwise, interacting with the outer bushing swirl impeller 115 ( Figure 6 Similar to ), it can be used with swirling fuel-air mixtures of 85 ( Figure 2 The swirl direction 87 is the same as or opposite to the direction of the airflow. Of course, the angle 166 of the inner bushing swirl vane 117 can be set to provide clockwise flow of compressed air 82(d) around the burner centerline 112. When the inner bushing swirl vane 117 is aligned as shown in Figure 7, and the outer bushing swirl vane 115 is aligned as shown in Figure 7... Figure 6When aligned as shown, the swirling flow of compressed air 82(d) supplied by the dilution opening 114 of the annular outer bushing groove and the swirling flow of compressed air 82(d) supplied by the dilution opening 116 of the annular inner bushing groove are in opposite directions. Of course, the outer bushing swirling impeller 115 and the inner bushing swirling impeller 117 can be arranged such that the compressed air 82(d) supplied by the dilution opening 114 of the annular outer bushing groove and the dilution opening 116 of the annular inner bushing groove flows in the same direction. Although Figure 7 The circumferential distance 170 and angle 166 of each of the plurality of liner swirl blades 117 shown may appear the same, as will be described below, but the angle 166 and circumferential distance 170 between each liner swirl blade 117 may vary.

[0046] Figure 8 Is Figure 6 A close-up view of the outer bushing swirl vane 115, taken at detail 172. (See also...) Figure 8 As shown, the outer bushing swirl vane 115 can be a linear vane having a linear profile extending between the outer bushing swirl vane inlet end 174 and the outer bushing swirl vane rear end 176. Furthermore, the first outer bushing swirl vane 182 and the second outer bushing swirl vane sidewall 184 can extend axially (e.g., perpendicular to the downstream side 158 of the annular outer bushing radial wall 146). Alternatively, the outer bushing swirl vane 115 is not a linear swirl vane, but can be an outer bushing curved swirl vane 178, wherein the rear end 180 can have a curved profile instead of the linear profile of the outer bushing swirl vane 115.

[0047] Figures 9A to 9C An alternative arrangement of the outer bushing swirl vane 115 is depicted. More detailed, Figures 9A to 9C The linear profile outer bushing swirl vane 115 is depicted extending axially from the radial wall 146 of the annular outer bushing to the outer bushing 54 within the annular outer bushing groove dilution opening 114, passing through... Figure 8 A cross-sectional view of the linear profile outer bushing swirl impeller 115. Figures 9A to 9C In the middle, not the first outer bushing swirl impeller sidewall 182 and the second outer bushing swirl impeller sidewall 184 extend perpendicularly to the downstream side 158 of the annular outer bushing radial wall 146 along the entire length from the outer bushing swirl impeller inlet end 174 to the outer bushing swirl impeller rear end 176. Figure 8 Instead, the sidewalls 182 / 184 can have an inclination that gradually increases along the length of the outer bushing impeller blades 115. Therefore, in Figure 9A In the cross-section (taken near the inlet end 174 of the outer bushing swirl impeller), the first outer bushing swirl impeller sidewall 182 and the second outer bushing swirl impeller sidewall 184 can be perpendicular to the downstream side 158 of the annular outer bushing radial wall 146. However, at the middle portion 186 of the outer bushing swirl impeller 115, as... Figure 9B As shown, the first outer bushing swirl vane sidewall 182 and the second outer bushing swirl vane sidewall 184 can be inclined at an angle 188 relative to the downstream side 158 of the annular outer bushing radial wall 146. In 9C (a cross-section taken near the rear end 176 of the outer bushing swirl vane), the first outer bushing swirl vane sidewall 182 and the second outer bushing swirl vane sidewall 184 can be inclined at an angle 190 relative to the downstream side 158 of the annular outer bushing radial wall 146, wherein angle 190 is steeper than angle 188. Although Figure 8 and 9A The above description up to 9C is directed at the outer bushing swirl impeller 115, but it is readily understood that these aspects also apply to the inner bushing swirl impeller 117. Therefore, the description of the inner bushing swirl impeller 117 is omitted here.

[0048] Figures 10A to 10C An alternative arrangement of the outer bushing swirl vane 115 is depicted. More detailed, Figures 10A to 10C The linear profile outer bushing swirl vane 115 is depicted extending axially from the radial wall 146 of the annular outer bushing to the outer bushing 54 within the annular outer bushing groove dilution opening 114, passing through... Figure 5 A cross-sectional view of the linear profile outer bushing swirl impeller 115. Figures 10A to 10C The cross-section of the outer bushing swirl vane 115 shown is taken through the same outer bushing swirl vane 115, but passes through the swirl vane 115 at different axial positions. Therefore, for example, Figures 10A to 10C The cross-section of the outer bushing swirl vane 115 on the left side of each of them is the same cross-section of the swirl vane 115. Figure 10A It is a cross-section of the longitudinal downstream portion 169 taken at the downstream side 151 of the dilution opening 114 of the annular outer bushing groove. For example... Figure 10A As shown, near the downstream side 151, the outer bushing swirl vane 115 is arranged radially (i.e., extending in the radial direction R) between the inlet end 153 and the outlet end 155 of the outer bushing swirl vane 115. Therefore, the dilution opening 114 of the annular outer bushing groove near the downstream side 151 ( Figure 4 The flow of compressed air 82(d) can be kept closer to the downstream side and helps to reduce the swirling on the downstream side of the annular outer bushing groove dilution opening 114 to prevent hot gas on the outer bushing hot side surface 124 of the outer bushing from being washed.

[0049] However, in such Figure 10BIn the middle portion 165 of the outer bushing swirl impeller 115 shown in the cross-section, a curved portion 157 is included in the outer bushing swirl impeller 115 facing the outlet end 155. The curved portion 157 of the middle portion 165 can be arranged at an angle 159 to induce swirl in the compressed air flow 82(d) having a first swirl number. In the upstream portion 167 of the outer bushing swirl impeller 115 near the upstream side 150 of the annular outer bushing groove dilution opening 114, as... Figure 10C As shown, a second curved portion 161 may be included toward the outlet end 155, and the angle 163 of the second curved portion 161 may be set to introduce a swirl with a second swirl number greater than the first swirl number into the compressed air flow 82(d) at the upstream end 150.

[0050] Figure 11 Depicting another aspect of this disclosure Figure 4 A detailed view taken at 200° shows an alternative arrangement of the outer and inner bushing grooves, dilution openings, and swirl impeller blades. Figure 11 In the middle, the outer bushing 54 includes an annular outer bushing groove dilution opening 114, a plurality of outer bushing swirl vanes 115 disposed therein, a second annular outer bushing groove dilution opening 118, and an annular outer bushing radial wall 146. However, in Figure 11 In the arrangement, the radial wall 192 of the second annular outer bushing is located on the downstream side 194 of the dilution opening 114 of the annular outer bushing groove. Figure 11 The annular outer bushing radial wall 146 and the second annular outer bushing radial wall 192 extend radially into the combustion chamber 62 perpendicular to the axial direction, and a plurality of outer bushing swirl vanes 115 are disposed between the annular outer bushing radial wall 146 and the second annular outer bushing radial wall 192.

[0051] Similarly, in Figure 11 In the middle, the inner liner 52 includes an annular inner liner groove dilution opening 116, a plurality of inner liner swirl vanes 117 disposed therein, a second annular inner liner groove dilution opening 119 disposed on the upstream side 145 of the annular inner liner radial wall 148, and the annular inner liner radial wall 148. However, in Figure 11 In the arrangement, the radial wall 196 of the second annular inner bushing is located at the downstream side 198 of the dilution opening 116 of the annular inner bushing groove. Figure 11 The annular inner liner radial wall 148 and the second annular inner liner radial wall 196 extend radially into the combustion chamber 62 perpendicular to the axial direction, and a plurality of inner liner swirl vanes 117 are disposed between the annular inner liner radial wall 148 and the second annular inner liner radial wall 196.

[0052] Figure 12 Depicting another aspect of this disclosure Figure 4A detailed view taken at 200° shows another arrangement of the outer and inner bushing grooves, dilution openings, and swirl impeller blades. Similar to... Figure 11 aspect, Figure 12 The components include an annular outer bushing groove dilution opening 114, multiple outer bushing swirl vanes 115, an annular outer bushing radial wall 146, a second annular outer bushing groove dilution opening 118, and a second annular outer bushing radial wall 192. However, Figure 12 aspect and Figure 11 One difference between the two aspects is that the aforementioned elements are not arranged perpendicular to the axial direction, but rather aligned at a downstream angle 202 to provide a downstream flow of compressed air 82(d) within the combustion chamber 62. Therefore, each of the annular outer bushing groove dilution opening 114, the plurality of outer bushing swirl vanes 115, the annular outer bushing radial wall 146, the second annular outer bushing groove dilution opening 118, and the second annular outer bushing radial wall 192 is arranged at a downstream angle 202. In this respect, the swirl of compressed air 82(d) exiting the plurality of outer bushing swirl vanes 115 can be configured to be closer to the outer bushing hot surface side 124 of the outer bushing 54 to provide surface cooling for the outer bushing 154.

[0053] Similarly, with Figure 11 Similar to the previous type, the inner liner 52 includes an annular inner liner groove dilution opening 116, a plurality of inner liner swirl vanes 117, an annular inner liner radial wall 148, a second annular inner liner groove dilution opening 119, and a second annular inner liner radial wall 196. However, Figure 12 aspect and Figure 11 One difference between the two aspects is that the aforementioned elements are not arranged perpendicular to the axial direction, but rather aligned at a downstream angle 204. Therefore, each of the annular inner liner groove dilution opening 116, the plurality of inner liner swirl vanes 117, the annular inner liner radial wall 148, the second annular inner liner groove dilution opening 119, and the second annular inner liner radial wall 196 is arranged at a downstream angle 204. In this respect, the swirl of compressed air 82(d) exiting the plurality of inner liner swirl vanes 117 can be configured to be closer to the inner liner hot surface side 128 of the inner liner 52 to provide surface cooling for the inner liner 52.

[0054] Figure 13 Depicting another aspect of this disclosure in Figure 4 A detailed view taken at 200° shows another arrangement of the outer and inner bushing grooves, dilution openings, and swirl impeller blades. Figure 13 In terms of, and Figure 11 Similarly, the outer bushing 54 includes an annular outer bushing groove dilution opening 114, a plurality of outer bushing swirl vanes 115, an annular outer bushing radial wall 146, a second annular outer bushing groove dilution opening 118, and a second annular outer bushing radial wall 192. However, Figure 13 aspect and Figure 11One difference between the two is that a second plurality of outer bushing swirl vanes 206 are disposed within the second annular outer bushing groove dilution opening 118. Each of the second plurality of outer bushing swirl vanes 206 may extend in the upstream direction from the upstream side 208 of the annular outer bushing radial wall 146 to the upstream side 210 of the second annular outer bushing groove dilution opening 118. The second plurality of outer bushing swirl vanes 206 may include a tapered radially inward portion 214, which is tapered and extends from the outer bushing hot surface side 124 at the upstream side 210 of the second annular outer bushing groove dilution opening 118 to the upstream side 208 of the annular outer bushing radial wall 146 at the radially inner end 212 of the annular outer bushing radial wall 146. Of course, the second plurality of outer bushing swirl vanes 206 need not include the conical radially inward portion 214, but may include an upstream edge 216 that extends radially inward to the radially inner end 212 of the annular outer bushing radial wall 146.

[0055] Similarly, the inner liner 52 includes an annular inner liner groove dilution opening 116, a plurality of inner liner swirl vanes 117, an annular inner liner radial wall 148, a second annular inner liner groove dilution opening 119, and a second annular inner liner radial wall 196. However, Figure 13 aspect and Figure 11 One difference lies in that the second plurality of inner liner swirl vanes 218 are disposed within the second annular inner liner groove dilution opening 119. Each of the second plurality of inner liner swirl vanes 218 may extend in the upstream direction from the upstream side 220 of the annular inner liner radial wall 148 to the upstream side 222 of the second annular inner liner groove dilution opening 119. The second plurality of inner liner swirl vanes 218 may include a tapered radially outer portion 224 that tapers from the inner liner hot surface side 128 at the upstream side 222 of the second annular inner liner groove dilution opening to the upstream side 220 of the annular inner liner radial wall 148 at the radially outer end 226 of the annular inner liner radial wall 148. Of course, the second plurality of inner liner swirl vanes 218 need not be tapered, but may include an upstream edge 228 extending radially inward to the radially outer end 226 of the annular inner liner radial wall 148.

[0056] Figure 14 Depicting another aspect of this disclosure in Figure 4 A detailed view taken at 200° shows another arrangement of the outer and inner bushing grooves, dilution openings, and swirl impeller blades. Figure 14The outer bushing 54 includes an annular outer bushing groove dilution opening 114, an annular outer bushing radial wall 146, a second annular outer bushing groove dilution opening 118, and a second plurality of outer bushing swirl vanes 206 disposed therein, having a plurality of outer bushing swirl vanes 115 disposed therein. As described above, the second plurality of outer bushing swirl vanes 206 includes a tapered radially inward portion 214. The plurality of outer bushing swirl vanes 115 includes a tapered radial interior 230 extending from a downstream side 194 of the annular outer bushing groove dilution opening 114 at the outer bushing hot surface side 124 to a radially inner end 212 of the annular outer bushing radial wall 146 at a downstream side 158. This is similar to Figure 4 The arrangement of multiple outer bushing swirl vanes 115 is depicted in the image.

[0057] Similarly, Figure 14 The inner liner 52 includes an annular inner liner groove dilution opening 116 in which a plurality of inner liner swirl vanes 117 are disposed, an annular inner liner radial wall 148, a second annular inner liner groove dilution opening 119, and a second plurality of inner liner swirl vanes 218 disposed therein. As described above, the second plurality of inner liner swirl vanes 218 includes a tapered radial outer portion 224. The plurality of inner liner swirl vanes 117 includes a tapered radial inner portion 232 that extends from a downstream side 198 of the annular inner liner groove dilution opening 116 at the hot surface side 128 of the inner liner to a radial outer end 226 of the annular inner liner radial wall 148 at a downstream side 168 of the annular inner liner radial wall 148.

[0058] Figure 15 Depicting another aspect of this disclosure in Figure 4 A detailed view taken at 200° shows another arrangement of the outer and inner bushing grooves, dilution openings, and swirl impeller blades. (Compared to...) Figure 11 In the same respect, Figure 15 The outer bushing 54 includes an annular outer bushing groove dilution opening 114, an annular outer bushing radial wall 146, a second annular outer bushing radial wall 192, and a second annular outer bushing groove dilution opening 118 having a plurality of outer bushing swirl vanes 115 disposed therein. Each of these elements is related to... Figure 11The corresponding elements described are the same. However, in Figure 15, the outer bushing 54 further includes a third annular outer bushing groove dilution opening 234 at the downstream side 236 of the second annular outer bushing radial wall 192, and a third annular outer bushing radial wall 238 disposed at the downstream side 240 of the third annular outer bushing groove dilution opening 234 and extending radially into the combustion chamber 62 perpendicular to the axial direction. A second plurality of outer bushing swirl vanes 242 are disposed in the third annular outer bushing groove dilution opening 234 between the downstream side 236 of the second annular outer bushing radial wall 192 and the upstream side 244 of the third annular outer bushing radial wall 238. The first plurality of outer bushing swirl vanes 115 and the second plurality of outer bushing swirl vanes 242 may have the same swirl direction relative to each other, or may have opposite swirl directions relative to each other. Furthermore, the first plurality of outer bushing swirl vanes 115 may be arranged in the same or opposite swirl direction as the swirl direction 87 of the swirling fuel-air mixture 85. Figure 2 Furthermore, the second plurality of outer bushing swirl vanes 242 can be arranged in the same swirl direction or opposite swirl direction as the swirl direction of the swirling fuel-air mixture 85.

[0059] exist Figure 15 In the middle, the inner lining 52 is also with Figure 11 The same as shown, but further includes a third annular inner liner groove dilution opening 246 at the downstream side 248 of the second annular inner liner radial wall 196, and a third annular inner liner radial wall 250 disposed at the downstream side 252 of the third annular inner liner groove dilution opening 246 and extending radially into the combustion chamber 62 perpendicular to the axial direction. A second plurality of inner liner swirl vanes 254 are disposed in the third annular inner liner groove dilution opening 246, which is arranged between the downstream side 248 of the second annular inner liner radial wall 196 and the upstream side 256 of the third annular inner liner radial wall 250. The first plurality of inner liner swirl vanes 117 and the second plurality of inner liner swirl vanes 254 may have the same swirl direction relative to each other, or may have opposite swirl directions relative to each other. Furthermore, the first plurality of inner-lined swirl vanes 117 may be arranged in the same swirl direction or opposite swirl direction as the swirl direction of the swirling fuel-air mixture 85, and the second plurality of inner-lined swirl vanes 254 may be arranged in the same swirl direction or opposite swirl direction as the swirl direction of the swirling fuel-air mixture 85.

[0060] Figure 16 Depicting another aspect of this disclosure in Figure 4 A detailed view taken at 200° shows another arrangement of the outer and inner bushing grooves, dilution openings, and swirl impeller blades. Figure 16The outer bushing 54 includes an annular outer bushing groove dilution opening 114, a second annular outer bushing groove dilution opening 118, and a second annular outer bushing radial wall 192 having a plurality of outer bushing swirl vanes 115 disposed therein. Figure 16 The outer bushing 54 also includes an annular outer bushing radial wall 258 similar to the annular outer bushing radial wall 146, but which extends further into the outer flow channel 88 on the outer bushing cold surface side 122 of the outer bushing 54. The outer bushing 54 further includes a third annular outer bushing radial wall 260, which extends radially outward from the outer bushing cold surface side 122 into the outer flow channel 88 at the upstream side 210 of the second annular outer bushing groove dilution opening 118. A second plurality of outer bushing swirl vanes 262 are disposed in the second annular outer bushing groove dilution opening 118 between the annular outer bushing radial wall 258 and the third annular outer bushing radial wall 260. The trailing edge 264 of each of the plurality of outer bushing swirl vanes 115 is disposed adjacent to the radially inner end 266 of the annular outer bushing radial wall 258, and the trailing edge 268 of each of the second plurality of outer bushing swirl vanes 262 is disposed adjacent to the outer bushing cold surface side 122. Therefore, the radially inner portion 270 of the second annular outer bushing groove dilution opening 118 may be without swirl vanes and prevent the flame from remaining at the trailing edge 268 of the second plurality of outer bushing swirl vanes 262. Furthermore, the compressed air flow 82(c) from the second annular outer bushing groove dilution opening 118... Figure 5 It can shield the trailing edge 264 of multiple outer bushing swirl vanes 115, thereby preventing the flame from remaining at the trailing edge 264.

[0061] Figure 16 The inner liner 52 includes an annular inner liner groove dilution opening 116, a second annular inner liner groove dilution opening 119, and a second annular inner liner radial wall 196 having a plurality of inner liner swirl vanes 117 disposed therein. Figure 16The inner liner 52 also includes an annular inner liner radial wall 272 similar to the annular inner liner radial wall 148, but which extends further into the inner flow channel 90 on the inner liner cold surface side 126 of the inner liner 52. The inner liner 52 further includes a third annular inner liner radial wall 274 that extends radially inward from the inner liner cold surface side 126 at the upstream end 276 of the second annular inner liner groove dilution opening 119 into the inner flow channel 90. A second plurality of inner liner swirl vanes 278 are disposed in the second annular inner liner groove dilution opening 119 between the annular inner liner radial wall 272 and the third annular inner liner radial wall 274. The trailing edge 280 of each of the plurality of inner liner swirl vanes 117 is configured to be adjacent to the radially outer end 282 of the annular inner liner radial wall 272, and the trailing edge 284 of each of the second plurality of inner liner swirl vanes 278 is configured to be adjacent to the inner liner cold surface side 126. Therefore, the radially outer portion 286 of the second annular inner liner groove dilution opening 119 may be without swirl vanes and prevent the flame from remaining at the trailing edge 284 of the second plurality of inner liner swirl vanes 278. Furthermore, the compressed air flow 82(c) from the second annular inner liner groove dilution opening 119... Figure 5 It can shield the trailing edge 280 of multiple inner bushing swirl vanes 117, thereby preventing the flame from remaining at the trailing edge 280.

[0062] Figure 17 Depicting another aspect of this disclosure in Figure 4 A detailed view taken at 200° shows another arrangement of the outer and inner bushing grooves, dilution openings, and swirl impeller blades. Figure 17 Similar to Figure 16 Therefore, the same reference numerals will not be described here again. However, the outer bushing 54 Figure 17 aspect and Figure 16 One difference between the aspects involves Figure 16 The second annular outer bushing radial wall 192. In Figure 16 In this configuration, the second annular outer bushing radial wall 192 extends radially inward from the outer bushing hot surface side 124 of the outer bushing 54. In contrast, in... Figure 17 In the middle, the radial wall 288 of the second annular outer bushing extends radially outward from the cold surface side 122 of the outer bushing into the outer flow channel 88. Furthermore, the trailing edge 264 of the plurality of outer bushing swirl vanes 115 extends to the radially inner end 266 of the annular outer bushing radial wall 258. Figure 17 The trailing edge 264 of the middle one is disposed adjacent to the cold surface side 122 of the outer bushing, and is the same as the trailing edge 268 of the second plurality of outer bushing swirl vanes 262. In addition, the radial inner end 266 of the annular outer bushing radial wall 258 may be rounded or chamfered at the upstream side 290, and the radial wall 288 of the second annular outer bushing may also be rounded or chamfered at its radial inner end 292.

[0063] Figure 17 The inner liner 52 is also similar Figure 16 The inner liner, therefore, will not be described again here by the same reference numerals. However, the inner liner 52 Figure 17 aspect and Figure 16 One difference between the aspects involves Figure 15 The second annular inner bushing radial wall 196. In Figure 16, the second annular inner bushing radial wall 196 extends radially outward from the outer bushing hot surface side 124 of the inner bushing 54. In contrast, in Figure 17 In the middle, the second annular inner liner radial wall 294 extends radially inward from the cold surface side 126 of the inner liner into the inner flow channel 90. Furthermore, the trailing edge 280 of the plurality of inner liner swirl vanes 117 extends to the radially outer end 282 of the annular inner liner radial wall 272. Figure 17 The trailing edge 280 of the middle one is disposed adjacent to the cold surface side 126 of the inner liner, and is the same as the trailing edge 284 of the second plurality of inner liner swirl vanes 278. In addition, the radial outer end 282 of the annular inner liner radial wall 272 may be rounded or chamfered at the upstream side 296, and the radial wall 294 of the second annular inner liner may also be rounded or chamfered at its radial outer end 298.

[0064] Figure 18 Depicting another aspect of this disclosure in Figure 4 A detailed view taken at 200° shows another arrangement of the outer and inner bushing grooves, dilution openings, and swirl impeller blades. Figure 18 Similar to Figure 11 Therefore, the same reference numerals will not be used here again. However, Figure 18 outer bushing 54 and Figure 11 Some differences lie in the inclusion of a third annular outer bushing groove dilution opening 300 and a third annular outer bushing radial wall 304. The third annular outer bushing groove dilution opening 300 is located on the downstream side 302 of the second annular outer bushing radial wall 192 and has a second plurality of outer bushing swirl vanes 306 disposed therein. The aforementioned differences are similar to Figure 15 In this respect. However, with Figure 11 In the same aspect, the third annular outer bushing groove dilution opening 300, the second plurality of outer bushing swirl vanes 306 disposed therein, and the third annular outer bushing radial wall 304 are all arranged at a downstream angle 202.

[0065] Inner liner 52 Figure 18 The aspect is also similar Figure 11 Therefore, the same reference numerals will not be used here. However, Figure 18 Inner liner 52 and Figure 11Some differences lie in the inclusion of a third annular inner liner groove dilution opening 308 and a third annular inner liner radial wall 312, wherein the third annular inner liner groove dilution opening 308 is located on the downstream side 310 of the second annular inner liner radial wall 196 and has a second plurality of inner liner swirl vanes 314 disposed therein. The aforementioned differences are similar to... Figure 15 In this respect. However, with Figure 11 Similarly, the third annular inner liner groove dilution opening 308, the second plurality of inner liner swirl vanes 314 disposed therein, and the third annular inner liner radial wall 312 are all arranged at a downstream angle 204.

[0066] Figure 19 Depicting another aspect of this disclosure in Figure 4 A detailed view taken at 200° shows another arrangement of the outer and inner bushing grooves, dilution openings, and swirl impeller blades. Both the outer bushing 54 and the inner bushing 52... Figure 19 Similar to Figure 18 Therefore, the same reference numerals will not be used here. However, Figure 19 The outer bushing 54 and the inner bushing 52 are related to Figure 18 Some differences lie in the omission of the second annular outer bushing groove dilution opening 118 and the second annular inner bushing groove dilution opening 119. Furthermore, the annular outer bushing groove dilution opening 114, the third annular outer bushing groove dilution opening 300, the annular outer bushing radial wall 146, the second annular outer bushing radial wall 192, and the third annular outer bushing radial wall 304 all use an upstream angle 316 instead of a downstream angle 202. Figure 18 Similarly, the annular inner liner groove dilution port 116, the third annular inner liner groove dilution port 308, the annular inner liner radial wall 148, the second annular inner liner radial wall 196, and the third annular inner liner radial wall 312 are all arranged at an upstream angle 318 rather than a downstream angle 204. Figure 18 Arrangement.

[0067] Figure 20 Depicting another aspect of this disclosure in Figure 4 A detailed view taken at 200° shows another arrangement of the outer and inner bushing grooves, dilution openings, and swirl impeller blades. Outer bushing 54 Figure 20The outer bushing 54 includes an annular outer bushing groove dilution opening 114, an annular outer bushing radial wall 146, and a second annular outer bushing radial wall 192, each arranged at a downstream angle 202, having a second plurality of outer bushing swirl vanes 322 disposed therein. The outer bushing 54 further includes a second annular outer bushing groove dilution opening 320, having a second plurality of outer bushing swirl vanes 322 disposed therein, wherein the second annular outer bushing groove dilution opening 320 is disposed between a third annular outer bushing radial wall 324 and a fourth annular outer bushing radial wall 326. The third annular outer bushing radial wall 324 is disposed downstream of the second annular outer bushing radial wall 192. The second annular outer bushing groove dilution opening 320, the third annular outer bushing radial wall 324, and the fourth annular outer bushing radial wall 326 are all arranged at an upstream angle 316. Therefore, the compressed air flow 82(d) through the annular outer bushing groove dilution opening 114 and the compressed air flow 82(d) through the second annular outer bushing groove dilution opening 320 converge at the outer bushing hot surface side 124 in the combustion chamber 62. Furthermore, the swirl directions of the plurality of outer bushing swirl vanes 115 and the plurality of outer bushing swirl vanes 322 can be in the same swirl direction relative to each other, or they can be in opposite swirl directions relative to each other.

[0068] Similarly, Figure 20 The inner liner 52 includes an annular inner liner groove dilution opening 116, an annular inner liner radial wall 148, and a second annular inner liner radial wall 196, each arranged at a downstream angle 204, having a plurality of inner liner swirl vanes 330 disposed therein. The inner liner 52 further includes a second annular inner liner groove dilution opening 328, having a second plurality of inner liner swirl vanes 330 disposed therein, wherein the second annular inner liner groove dilution opening 328 is disposed between a third annular inner liner radial wall 332 and a fourth annular inner liner radial wall 334. The third annular inner liner radial wall 332 is disposed downstream of the second annular inner liner radial wall 196. The second annular inner liner groove dilution opening 328, the third annular inner liner radial wall 332, and the fourth annular inner liner radial wall 334 are all arranged at an upstream angle 318. Therefore, the compressed air flow 82(d) through the annular inner liner groove dilution opening 116 and the compressed air flow 82(d) through the second annular inner liner groove dilution opening 328 converge at the inner liner hot surface side 128 in the combustion chamber 62. Furthermore, the swirl directions of the plurality of inner liner swirl vanes 117 and the plurality of inner liner swirl vanes 330 can be in the same swirl direction relative to each other, or they can be in opposite swirl directions relative to each other.

[0069] Figure 21 Depicting another aspect of this disclosure in Figure 4 A detailed view taken at 200° shows another arrangement of the outer and inner bushing grooves, dilution openings, and swirl impeller blades. Figure 21 The outer bushing 54 includes an annular outer bushing groove dilution opening 114, which has a plurality of outer bushing swirl vanes 115 disposed therein between the annular outer bushing radial wall 146 and the second annular outer bushing radial wall 192. Figure 21 In terms of the outer bushing, both the annular outer bushing radial wall 146 and the second annular outer bushing radial wall 192 extend radially outward from the cold surface side 122 of the outer bushing into the outer flow channel 88. The trailing edge 336 of each of the plurality of outer bushing swirl vanes 115 is considered to be located radially outward from the cold surface side 122 of the outer bushing, or may be arranged adjacent to the cold surface side 122 of the outer bushing. Therefore, the radially inner portion 338 of the annular outer bushing groove dilution opening 114 remains without swirl vanes to prevent the flame from remaining at the trailing edge 336.

[0070] Similarly, Figure 21 The inner liner 52 includes an annular inner liner groove dilution opening 116, which has a plurality of inner liner swirl vanes 117 disposed therein between the annular inner liner radial wall 148 and the second annular inner liner radial wall 196. Figure 21 In terms of the annular inner liner radial wall 148 and the second annular inner liner radial wall 196, both extend radially inward from the cold surface side 126 of the inner liner into the inner flow channel 90. The trailing edge 340 of each of the plurality of inner liner swirl vanes 117 is considered to be located radially inside the cold surface side 126 of the inner liner, or may be arranged adjacent to the cold surface side 126 of the inner liner. Therefore, the radially inner portion 342 of the annular inner liner groove dilution opening 116 remains without swirl vanes to prevent the flame from remaining at the trailing edge 340.

[0071] Figure 22 Depicting another aspect of this disclosure in Figure 4 Another arrangement of the outer and inner liner grooves, dilution openings, and swirl impeller blades, cut at plane 22-22. (See above regarding...) Figure 3 In brief, the burner bushing 50 can be considered to be divided into multiple segments around the burner centerline 112. Figure 12 The image depicts a section taken at plane 22-22 passing through the dilution opening 114 of the annular outer groove and the dilution opening 116 of the annular inner liner groove. Figure 3 The first segment 129. As briefly discussed above, each segment includes a corresponding segment cyclone assembly 58, and in Figure 12In this context, the corresponding cyclone assembly 58 of the first segment 129 is cyclone assembly 58(a). Furthermore, as described above, each burner bushing segment defines a first end extending radially from the burner centerline 112 and a second end extending radially from the burner centerline 112 and circumferentially spaced from the first end. For the first segment 129, the first end 382 can be considered to correspond to the segment boundary line 134, and the second end 384 can be considered to correspond to the segment boundary line 136. Additionally, as previously stated, each segment includes an outer bushing segment portion of the outer bushing 54 (e.g., the first segment outer bushing 130) and an inner bushing segment portion of the inner bushing 52 (e.g., the first segment inner bushing 140). The first segment outer bushing 130 includes an outer bushing segment radial wall 344 of an annular outer bushing radial wall 146, and the first segment inner bushing 140 includes an inner bushing segment radial wall 346 of an annular inner bushing radial wall 148. The outer bushing section radial wall 344 includes a plurality of outer bushing swirl vanes 115 disposed in a first circumferential region 348 of the outer bushing section radial wall 344, but not included in a plurality of outer bushing swirl vanes 115 disposed in a second circumferential region 350 of the outer bushing section radial wall 344. On the other hand, the inner bushing section radial wall 346 does not include a plurality of inner bushing swirl vanes 117 disposed in a first circumferential region 352 of the inner bushing section radial wall 346, but includes a plurality of inner bushing swirl vanes 117 disposed in a second circumferential region 354 of the inner bushing section radial wall 346. The first circumferential region 348 of the outer bushing section radial wall 344 and the first circumferential region 352 of the inner bushing section radial wall 346 are radially opposite each other across the combustion chamber 62, and the second circumferential region 350 of the outer bushing section radial wall 344 and the second circumferential region 354 of the inner bushing section radial wall 346 are radially opposite each other across the combustion chamber 62. However, as Figure 22 As shown, the first circumferential region 348 of the radial wall 344 of the outer liner section can circumferentially overlap with the second circumferential region 354 of the radial wall 346 of the inner liner section.

[0072] Multiple outer bushing swirl vanes 115 in the first circumferential region 348 of the radial wall 344 of the outer bushing section are configured to provide oxidant 356 (i.e., compressed air 82(d)) into the combustion chamber 62 around the central axis 144 of the first swirler assembly 58(a) in the first circumferential swirling direction 358. Figure 21In this configuration, the first circumferential swirling direction 358 is counterclockwise around the central axis 144 of the cyclone assembly and extends axially. To provide oxidant flow in the first circumferential swirling direction, each of the plurality of outer bushing swirling blades 115 disposed in the first circumferential region 348 of the radial wall 344 of the outer bushing section is arranged at a different circumferential angle relative to the central axis 144 of the cyclone assembly. For example, the first outer bushing swirling blade 360 ​​may be arranged at a first angle 362, and the second outer bushing swirling blade 364 may be arranged at a second angle 366, wherein the first angle 362 is different from the second angle 366. In contrast, in the second circumferential region 350 of the radial wall 344 of the outer bushing section excluding the outer bushing swirling blades 115, a radial flow 368 of oxidant is provided to the combustion chamber 62.

[0073] Similarly, a plurality of inner liner swirl vanes 117 in the second circumferential region 354 of the radial wall 346 of the inner liner section are configured to provide an inner liner section swirl of oxidant 380 into the combustion chamber 62 around the central axis 144 of the first section swirler assembly 58(a) along a first circumferential swirl direction 358. To provide oxidant flow in the first circumferential swirl direction 358, each inner liner swirl vane 117 among a plurality of outer liner swirl vanes disposed in the second circumferential region 354 of the radial wall 346 of the inner liner section is arranged at a different circumferential angle relative to the central axis 144 of the section swirler assembly. For example, the first inner liner swirl vane 370 may be arranged at a first angle 372, and the second inner liner swirl vane 374 may be arranged at a second angle 376, wherein the first angle 372 is different from the second angle 376. In contrast, in the first circumferential region 352 of the radial wall 346 of the inner liner section excluding the inner liner swirl vane 117, a radial flow 378 of oxidant is provided to the combustion chamber 62.

[0074] While the foregoing description generally pertains to gas turbine engines, it is readily understood that gas turbine engines can be implemented in a variety of environments. For example, the engine can be implemented in aircraft, but it can also be implemented in non-aircraft applications, such as power plants, marine applications, or oil and gas production applications. Therefore, this disclosure is not limited to use in aircraft.

[0075] Further aspects of this disclosure are provided by the subject matter of the following clauses.

[0076] A burner bushing for a gas turbine burner, the burner bushing defining an axial direction, a radial direction, and a circumferential direction about a burner centerline, the burner bushing comprising: an outer bushing extending circumferentially about the burner centerline and extending along the axial direction from an upstream end to a downstream end of the outer bushing; an outer bushing dilution zone defined between the upstream and downstream ends of the outer bushing; the outer bushing having a cold surface side and a hot surface side, and defining an outer bushing flow direction along the axial direction from the upstream to the downstream end of the outer bushing; the outer bushing including an annular outer bushing groove dilution opening through the outer bushing in the outer bushing dilution zone, the annular outer bushing groove dilution opening comprising a plurality of [missing information]. An outer bushing swirl vane; and an inner bushing extending circumferentially around the burner centerline and extending axially from an upstream end to a downstream end of the inner bushing, a bushing dilution zone defined between the upstream and downstream ends of the inner bushing, the inner bushing having a cold surface side and a hot surface side, defining a bushing flow direction extending axially from the upstream to the downstream end of the inner bushing, and the inner bushing including an annular bushing groove dilution opening through the bushing in the bushing dilution zone, the annular bushing groove dilution opening including a plurality of bushing swirl vanes therein, wherein a combustion chamber is defined between the hot surface side of the outer bushing and the hot surface side of the inner bushing.

[0077] According to any one of the preceding claims, the burner bushing comprises: (a) a first outer bushing radial wall disposed downstream of the dilution opening of the annular outer bushing groove and extending radially outward from the cold surface side of the outer bushing into an external flow channel adjacent to the cold surface side of the outer bushing; and (b) a second outer bushing radial wall disposed upstream of the dilution opening of the annular outer bushing groove and extending radially outward from the cold surface side of the outer bushing into the external flow channel adjacent to the cold surface side of the outer bushing, wherein the plurality of outer bushing swirl vanes are disposed between the first outer bushing radial wall and the second outer bushing radial wall, and the trailing edge of each of the plurality of outer bushing swirl vanes is adjacent to the... The outer bushing is disposed on the cold surface side, and the inner bushing includes: (a) a first inner bushing radial wall disposed downstream of the dilution opening of the annular inner bushing groove and extending radially inward from the cold surface side of the inner bushing into an inner flow channel adjacent to the cold surface side of the inner bushing; and (b) a second inner bushing radial wall disposed upstream of the dilution opening of the annular inner bushing groove and extending radially inward from the cold surface side of the inner bushing into the inner flow channel adjacent to the cold surface side of the inner bushing, the plurality of inner bushing swirl vanes disposed between the first inner bushing radial wall and the second inner bushing radial wall, the trailing edge of each of the plurality of inner bushing swirl vanes being disposed adjacent to the cold surface side of the inner bushing.

[0078] The burner bushing according to any one of the preceding clauses, wherein the outer bushing comprises: (a) a first annular outer bushing radial wall disposed upstream of the dilution opening of the annular outer bushing groove; (b) a second annular outer bushing radial wall disposed downstream of the dilution opening of the annular outer bushing groove, the first and second annular outer bushing radial walls extending at a downstream angle relative to the burner centerline and radially into an external flow channel on the cold surface side of the outer bushing; (c) a third annular outer bushing radial wall disposed downstream of the second annular outer bushing radial wall; and (d) a fourth annular outer bushing radial wall. The outer bushing radial wall, the fourth annular outer bushing radial wall being disposed downstream of the third annular outer bushing radial wall, the third and fourth annular outer bushing radial walls extending radially upstream relative to the burner centerline into the external flow channel on the cold surface side of the outer bushing; (e) a second annular outer bushing groove dilution opening defined between the third and fourth annular outer bushing radial walls; and (f) a second plurality of outer bushing swirl vanes disposed within the second annular outer bushing groove dilution opening, the annular outer bushing groove dilution opening and the second annular outer bushing groove dilution opening being arranged on the hot surface side of the outer bushing. Provides a converging flow of oxidant, and the liner includes: (a) a first annular liner radial wall disposed upstream of the annular liner groove dilution opening; (b) a second annular liner radial wall disposed downstream of the annular liner groove dilution opening, the first and second annular liner radial walls extending radially downstream relative to the burner centerline into an inner flow channel on the liner's cold surface side; (c) a third annular liner radial wall disposed downstream of the second annular liner radial wall; and (d) a fourth annular liner radial wall, the first annular liner radial wall being disposed downstream of the second annular liner radial wall. (e) A fourth annular inner liner radial wall is disposed downstream of the third annular inner liner radial wall, the third annular inner liner radial wall and the fourth annular inner liner radial wall extending at an upstream angle relative to the burner centerline and radially upstream into an inner flow channel on the cold surface side of the inner liner; and (f) a second annular inner liner groove dilution opening defined between the third annular inner liner radial wall and the fourth annular inner liner radial wall; and (f) a second plurality of inner liner swirl vanes disposed within the second annular inner liner groove dilution opening, the annular inner liner groove dilution opening and the second annular inner liner groove dilution opening being arranged to provide a converging flow of oxidant on the hot surface side of the inner liner.

[0079] According to any one of the preceding claims, the burner bushing comprises a plurality of outer bushing swirl vanes arranged to generate oxidant swirl in the combustion chamber relative to the circumferential direction along a first direction, and a plurality of inner bushing swirl vanes arranged to generate oxidant in the combustion chamber relative to the circumferential direction along a second direction, the first direction being opposite to the second direction circumferentially around the burner centerline. The first and second directions are in the same circumferential direction around the burner centerline.

[0080] According to any one of the preceding clauses, a plurality of outer bushing swirl vanes are arranged to generate an oxidant swirl in the combustion chamber relative to a circumferential direction along a first direction, and a plurality of inner bushing swirl vanes are arranged to generate an oxidant swirl in the combustion chamber relative to a circumferential direction along a second direction, the first direction being the opposite direction to the second direction circumferentially surrounding the burner centerline.

[0081] The burner bushing according to any one of the preceding clauses, wherein the outer bushing includes an annular outer bushing radial wall disposed upstream of the annular outer bushing groove dilution opening and extending at least partially from the outer bushing into the combustion chamber in the radial direction, and the inner bushing includes an annular inner bushing radial wall disposed upstream of the annular inner bushing groove dilution opening and extending at least partially into the combustion chamber in the radial direction.

[0082] The burner bushing according to any one of the preceding claims, wherein the burner bushing comprises a plurality of burner bushing segments circumferentially arranged around the burner centerline, each burner bushing segment being associated with a corresponding segment of a plurality of swirler assemblies circumferentially spaced around the burner centerline, and each burner bushing segment defining a first end extending from the burner centerline in the radial direction and a second end extending from the burner centerline in the radial direction and circumferentially spaced from the first end of the segment, each segment comprising an outer bushing segment portion of the outer bushing and an inner bushing segment portion of the inner bushing, the outer bushing segment portion comprising the radial wall of the annular outer bushing radial wall, and the inner bushing comprising the radial wall of the annular inner bushing radial wall. In the combustion chamber, the radial wall of the outer bushing section includes a plurality of outer bushing swirl vanes disposed in a first circumferential region of the radial wall of the outer bushing section, but not including the plurality of outer bushing swirl vanes in a second circumferential region of the radial wall of the outer bushing section. Similarly, the radial wall of the inner bushing section does not include the plurality of inner bushing swirl vanes in the first circumferential region of the radial wall of the inner bushing section, but includes the plurality of inner bushing swirl vanes in the second circumferential region of the radial wall of the inner bushing section. The first circumferential region of the outer bushing section and the first circumferential region of the inner bushing section are radially opposite each other across the combustion chamber, and the second circumferential region of the outer bushing section and the second circumferential region of the inner bushing section are radially opposite each other across the combustion chamber.

[0083] According to any one of the preceding claims, the burner bushing, wherein the plurality of outer bushing swirl vanes in the first circumferential region of the radial wall of the outer bushing section are configured to provide oxidant to the combustion chamber through the outer bushing section in a first circumferential swirl direction surrounding the swirler centerline axis of the swirler, the swirler centerline axis extending in the axial direction, and the plurality of inner bushing swirl vanes in the second circumferential region of the radial wall of the inner bushing section are configured to provide oxidant to the combustion chamber through the inner bushing section in the first circumferential swirl direction.

[0084] According to any one of the preceding clauses, the outer liner radial flow of oxidant is provided along the radial direction through the second circumferential region of the radial wall of the outer liner segment, and the inner liner radial flow of oxidant is provided along the radial direction through the first circumferential region of the radial wall of the inner liner segment.

[0085] According to any one of the preceding clauses, in the burner bushing, each of the plurality of outer bushing swirl vanes disposed in the first circumferential region of the radial wall of the outer bushing section is arranged at a different circumferential angle relative to the central axis of the section swirler, and each of the plurality of inner bushing swirl vanes disposed in the second circumferential region of the radial wall of the inner bushing section is arranged at a different circumferential angle relative to the central axis of the section swirler.

[0086] The burner bushing according to any one of the preceding clauses, wherein the outer bushing further includes a second annular outer bushing groove dilution port disposed on the upstream side of the radial wall of the annular outer bushing, and the inner bushing further includes a second annular inner bushing groove dilution opening disposed on the upstream side of the radial wall of the annular inner bushing.

[0087] According to any one of the preceding clauses, the burner bushing, wherein the second annular outer bushing groove dilution opening includes a second plurality of outer bushing swirl vanes, the conical radially inner portions of the plurality of outer bushing swirl vanes extending from the downstream side of the annular outer bushing groove dilution opening at the hot surface side of the outer bushing to the radially inner end of the annular outer bushing radial wall, and the conical radially inner portions of the second plurality of outer bushing swirl vanes extending from the upstream side of the second annular groove dilution opening at the hot surface side of the outer bushing to the annular outer bushing diameter... The radially inner end of the wall, and the second annular inner liner groove dilution opening includes a second plurality of inner liner swirl vanes, wherein the conical radially outer portions of the plurality of inner liner swirl vanes extend from the downstream side of the inner liner groove dilution opening at the hot surface side of the inner liner to the radially outer end of the annular inner liner radial wall, and the conical radially outer portions of the second plurality of inner liner swirl vanes extend from the upstream side of the second annular groove dilution opening at the hot surface side of the inner liner to the radially outer end of the annular inner liner radial wall.

[0088] According to any one of the preceding clauses, the burner bushing, wherein the annular outer bushing radial wall further extends into the outer flow channel on the cold surface side of the outer bushing, and the outer bushing further comprises: (a) a second annular outer bushing radial wall disposed downstream of the dilution opening of the annular outer bushing groove and extending radially outward from the cold surface side of the outer bushing into the outer flow channel, the plurality of outer bushing swirl vanes disposed between the annular outer bushing radial wall and the second annular outer bushing radial wall; (b) a third outer bushing radial wall, The third outer bushing radial wall is disposed upstream of the second annular outer bushing groove dilution opening and extends radially outward from the cold surface side of the outer bushing into the outer flow channel; (c) a second plurality of outer bushing swirl vanes, the second plurality of outer bushing swirl vanes being disposed in the second annular outer bushing groove dilution opening between the annular outer bushing radial wall and the third annular outer bushing radial wall, the trailing edge of each of the plurality of outer bushing swirl vanes being disposed adjacent to the cold surface side of the outer bushing, and the trailing edge of each of the second plurality of outer bushing swirl vanes being adjacent to the outer bushing The annular inner liner is disposed on the cold surface side, and the radial wall of the annular inner liner further extends into the inner flow channel on the cold surface side of the inner liner, and the inner liner further includes: (a) a second annular inner liner radial wall disposed downstream of the dilution opening of the annular inner liner groove and extending radially inward from the cold surface side of the inner liner into the inner flow channel, the plurality of inner liner swirl vanes being disposed between the annular inner liner radial wall and the second annular inner liner radial wall; (b) a third annular inner liner radial wall, the third annular inner liner radial wall being... (c) A second plurality of inner liner swirl vanes, wherein the second plurality of inner liner swirl vanes are disposed in the second annular inner liner groove dilution opening between the radial wall of the annular inner liner and the radial wall of the third annular inner liner, wherein the trailing edge of each of the plurality of inner liner swirl vanes is disposed adjacent to the cold surface side of the inner liner, and the trailing edge of each of the second plurality of inner liner swirl vanes is disposed adjacent to the cold surface side of the inner liner.

[0089] The burner bushing according to any one of the preceding clauses, wherein the trailing edge of each of the plurality of outer bushing swirl vanes extends from the radially inner end of the annular outer bushing radial wall to the downstream side of the annular outer bushing groove dilution opening at the outer bushing hot surface side of the outer bushing, and wherein the trailing edge of each of the plurality of inner bushing swirl vanes extends from the radially outer end of the annular inner bushing radial wall to the downstream side of the annular inner bushing groove dilution opening at the inner bushing hot surface side of the inner bushing.

[0090] The burner bushing according to any one of the preceding claims, wherein the outer bushing further includes a second annular outer bushing radial wall disposed downstream of the dilution opening of the annular outer bushing groove, the plurality of outer bushing swirl vanes arranged between the annular outer bushing radial wall and the second annular outer bushing radial wall, and the inner bushing further includes a second annular inner bushing radial wall disposed downstream of the dilution opening of the annular inner bushing groove, the plurality of inner bushing swirl vanes arranged between the annular inner bushing radial wall and the second annular inner bushing radial wall.

[0091] The burner bushing according to any one of the preceding clauses, wherein the outer bushing further comprises: (a) a third annular outer bushing radial wall disposed upstream of the second annular outer bushing groove dilution opening and extending at least partially into an external flow channel on the cold surface side of the outer bushing; and (b) a second plurality of outer bushing swirl vanes disposed in the second annular outer bushing groove dilution opening between the third annular outer bushing radial wall and the annular outer bushing radial wall, the annular outer bushing radial wall further extending at least partially into an external flow channel on the cold surface side of the outer bushing; and (b) a second plurality of outer bushing swirl vanes disposed in the second annular outer bushing groove dilution opening between the third annular outer bushing radial wall and the annular outer bushing radial wall, the annular outer bushing radial wall further extending at least partially into an external flow channel on the cold surface side of the outer bushing; The inner liner further comprises: (a) a third annular inner liner radial wall disposed upstream of the second annular inner liner groove dilution opening and extending at least partially into the inner flow channel on the cold surface side of the inner liner; and (b) a second plurality of inner liner swirl vanes disposed in the second annular inner liner groove dilution opening between the third annular inner liner radial wall and the annular inner liner radial wall, the annular inner liner radial wall further extending at least partially into the inner flow channel.

[0092] The burner bushing according to any one of the preceding clauses, wherein the radial wall of the annular outer bushing and the radial wall of the second annular outer bushing extend into the combustion chamber at a downstream angle relative to the radial direction, and the radial wall of the annular inner bushing and the radial wall of the second annular inner bushing extend into the combustion chamber at a downstream angle relative to the radial direction.

[0093] The burner bushing according to any one of the preceding claims, wherein the outer bushing further comprises: (a) a third annular outer bushing groove dilution opening disposed downstream of the radial wall of the second annular outer bushing; and (b) a third annular outer bushing radial wall disposed downstream of the third annular outer bushing groove dilution opening and extending at a downstream angle relative to the radial direction into the combustion chamber; and (c) a second plurality of outer bushing swirl vanes disposed in the third annular outer bushing groove dilution opening, the third annular outer bushing groove dilution opening being arranged on the radial wall of the second annular outer bushing and the third annular outer bushing. Between the radial walls of the outer bushing, and the inner bushing further includes: (a) a third annular inner bushing groove dilution opening disposed downstream of the radial wall of the second annular inner bushing; and (b) a third annular inner bushing radial wall disposed downstream of the third annular inner bushing groove dilution opening and extending at a downstream angle relative to the radial direction into the combustion chamber; and (c) a second plurality of inner bushing swirl vanes disposed in the third annular outer bushing groove dilution opening, the third annular outer bushing groove dilution opening being arranged between the radial walls of the second annular inner bushing and the third annular inner bushing.

[0094] The burner bushing according to any one of the preceding clauses, wherein the radial wall of the annular outer bushing and the radial wall of the second annular outer bushing extend radially into the combustion chamber perpendicular to the axial direction, and the radial wall of the annular inner bushing and the radial wall of the second annular inner bushing extend radially into the combustion chamber perpendicular to the axial direction.

[0095] According to any one of the preceding clauses, the burner bushing, wherein the second annular outer bushing groove dilution opening includes a second plurality of outer bushing swirl vanes disposed on the upstream side of the radial wall of the annular outer bushing, and the second annular inner bushing groove dilution opening includes a second plurality of inner bushing swirl vanes disposed on the upstream side of the radial wall of the annular inner bushing.

[0096] The burner bushing according to any one of the preceding claims, wherein the outer bushing further comprises: (a) a third annular outer bushing groove dilution opening, the third annular outer bushing groove dilution opening being located downstream of the radial wall of the second annular outer bushing; (b) a third annular outer bushing radial wall, the third annular outer bushing radial wall being disposed downstream of the third annular outer bushing groove dilution opening and extending radially into the combustion chamber perpendicular to the axial direction; and (c) a second plurality of outer bushing swirl vanes, the second plurality of outer bushing swirl vanes being disposed in the third annular outer bushing groove dilution opening, the third annular outer bushing groove dilution opening being arranged on the radial wall of the second annular outer bushing and the third annular outer bushing. The inner liner further comprises: (a) a third annular inner liner groove dilution opening located downstream of the second annular inner liner radial wall; (b) a third annular inner liner radial wall disposed downstream of the third annular inner liner groove dilution opening and extending radially into the combustion chamber perpendicular to the axial direction; and (c) a second plurality of inner liner swirl vanes disposed in the third annular inner liner groove dilution opening, the third annular inner liner groove dilution opening being arranged between the second annular inner liner radial wall and the third annular inner liner radial wall.

[0097] According to any one of the preceding clauses, the burner bushing, wherein the annular outer bushing radial wall further extends into an external flow channel on the cold surface side of the outer bushing, and the outer bushing further comprises: (a) a third annular outer bushing radial wall extending radially outward from the cold surface side of the outer bushing at the upstream side of the second annular outer bushing groove dilution opening into the external flow channel; and (b) a second plurality of outer bushing swirl vanes disposed in the second annular outer bushing groove dilution opening between the annular outer bushing radial wall and the third annular outer bushing radial wall, wherein the trailing edge of each of the plurality of outer bushing swirl vanes is disposed adjacent to the radially inner end of the annular outer bushing radial wall, and the trailing edge of each of the second plurality of outer bushing swirl vanes is adjacent to the radially inner end of the annular outer bushing radial wall. The outer bushing is disposed on the cold surface side, and the annular inner bushing radial wall further extends into the inner flow channel on the cold surface side of the inner bushing, and the inner bushing further includes: (a) a third annular inner bushing radial wall, the third annular inner bushing radial wall extending radially inward from the inner bushing cold surface side at the upstream side of the second annular inner bushing groove dilution opening into the inner flow channel; and (b) a second plurality of inner bushing swirl vanes, the second plurality of inner bushing swirl vanes disposed in the second annular inner bushing groove dilution opening between the annular inner bushing radial wall and the third annular inner bushing radial wall, the trailing edge of each of the plurality of inner bushing swirl vanes being disposed adjacent to the radially outer end of the annular inner bushing radial wall, and the trailing edge of each of the second plurality of inner bushing swirl vanes being disposed adjacent to the inner bushing cold surface side.

[0098] According to any one of the preceding claims, each of the plurality of outer bushing swirl vanes extends along the axial direction between the upstream side of the annular outer bushing groove dilution opening and the downstream side of the annular groove dilution opening, and extends longitudinally in the radial direction; a downstream longitudinal portion of each of the plurality of outer bushing swirl vanes at the downstream side of the annular outer bushing groove dilution opening extends in the radial direction; a middle longitudinal portion of each of the plurality of outer bushing swirl vanes, at the axial midpoint of the outer bushing swirl vane, includes a first curved outlet end, the first curved outlet end being arranged at a first angle relative to the radial direction; and an upstream longitudinal portion of each of the plurality of outer bushing swirl vanes, at the upstream side of the annular outer bushing groove dilution opening, includes a second curved outlet end, the second curved outlet end being arranged at a second angle greater than the first angle.

[0099] While the foregoing description is provided for some exemplary embodiments of this disclosure, it should be noted that other changes and modifications will be apparent to those skilled in the art and can be made without departing from the spirit or scope of this disclosure. Furthermore, features described in connection with one embodiment of this disclosure can be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A combustor liner for a combustor of a gas turbine engine, the combustor comprising a combustion chamber, the combustor liner defining an axial direction, a radial direction, and a circumferential direction about a combustor centerline, characterized by, The combustor liner includes: an outer liner extending circumferentially about the combustor centerline and extending in the axial direction from an outer liner upstream end to an outer liner downstream end, an outer liner dilution zone defined between the outer liner upstream end and the outer liner downstream end, the outer liner having an outer liner cold surface side and an outer liner hot surface side and defining an outer liner flow direction extending in the axial direction from the outer liner upstream end to the outer liner downstream end, the outer liner including an annular outer liner radial wall at the outer liner dilution zone, the annular outer liner radial wall extending at least partially from the outer liner in the radial direction into the combustion chamber, the annular outer liner radial wall and the outer liner defining an annular outer liner slot dilution opening therebetween, the annular outer liner slot dilution opening extending through the outer liner, the annular outer liner radial wall and the annular outer liner slot dilution opening extending continuously in the circumferential direction about the combustor centerline, the annular outer liner slot dilution opening including a plurality of outer liner swirl vane blades therein, and an inner liner extending circumferentially about the combustor centerline and extending in the axial direction from an inner liner upstream end to an inner liner downstream end, an inner liner dilution zone defined between the inner liner upstream end and the inner liner downstream end, the inner liner having an inner liner cold surface side and an inner liner hot surface side and defining an inner liner flow direction extending in the axial direction from the inner liner upstream end to the inner liner downstream end, the inner liner including an annular inner liner radial wall at the inner liner dilution zone, the annular inner liner radial wall extending at least partially from the inner liner in the radial direction into the combustion chamber, the annular inner liner radial wall and the inner liner defining an annular inner liner slot dilution opening therebetween, the annular inner liner slot dilution opening extending through the inner liner, the annular inner liner radial wall and the annular inner liner slot dilution opening extending continuously in the circumferential direction about the combustor centerline, the annular inner liner slot dilution opening including a plurality of inner liner swirl vane blades therein, wherein the combustion chamber is defined between the outer liner hot surface side of the outer liner and the inner liner hot surface side of the inner liner.

2. The combustor liner according to claim 1, wherein, wherein, the outer liner includes: (a) the annular outer liner radial wall disposed on a downstream side of the annular outer liner slot dilution opening and extending radially outward from the outer liner cold surface side into an outer flow passage adjacent the outer liner cold surface side; and (b) a second outer liner radial wall disposed on an upstream side of the annular outer liner slot dilution opening and extending radially outward from the outer liner cold surface side into the outer flow passage adjacent the outer liner cold surface side, the plurality of outer liner swirl vane blades being disposed between the annular outer liner radial wall and the second outer liner radial wall, a trailing edge of each of the plurality of outer liner swirl vane blades being disposed adjacent the outer liner cold surface side, and The inner liner includes: (a) the annular inner liner radial wall disposed on a downstream side of the annular inner liner slot dilution opening and extending radially inward from the inner liner cold surface side into the inner flow passage adjacent the inner liner cold surface side; and (b) a second inner liner radial wall disposed on an upstream side of the annular inner liner slot dilution opening and extending radially inward from the inner liner cold surface side into the inner flow passage adjacent the inner liner cold surface side, the plurality of inner liner swirler vanes being disposed between the annular inner liner radial wall and the second inner liner radial wall, a trailing edge of each of the plurality of inner liner swirler vanes being disposed adjacent the inner liner cold surface side.

3. The combustor liner according to claim 1, wherein, wherein, each of the plurality of outer liner swirler vanes extends in the axial direction between an upstream side of the annular outer liner slot dilution opening to a downstream side of the annular outer liner slot dilution opening, and extends longitudinally in the radial direction, a downstream longitudinal portion of each of the plurality of outer liner swirler vanes at the downstream side of the annular outer liner slot dilution opening extends in the radial direction; a middle longitudinal portion of each of the plurality of outer liner swirler vanes, at an axial midpoint of each of the plurality of outer liner swirler vanes, includes a first curved outlet end arranged at a first angle relative to the radial direction; and an upstream longitudinal portion of each of the plurality of outer liner swirler vanes, at the upstream side of the annular outer liner slot dilution opening, includes a second curved outlet end arranged at a second angle greater than the first angle.

4. The combustor liner of claim 1, wherein wherein, the annular outer liner radial wall is disposed on an upstream side of the annular outer liner slot dilution opening, and the annular inner liner radial wall is disposed on an upstream side of the annular inner liner slot dilution opening.

5. The combustor liner according to claim 4, wherein, wherein, the combustor liner includes a plurality of combustor liner segments arranged circumferentially about the combustor centerline, each combustor liner segment being associated with a corresponding segment swirler assembly of a plurality of swirler assemblies circumferentially spaced about the combustor centerline, and each combustor liner segment defining a segment first end extending from the combustor centerline in the radial direction, and a segment second end extending from the combustor centerline in the radial direction and circumferentially spaced from the segment first end, each segment including an outer liner segment portion of the outer liner and an inner liner segment portion of the inner liner, the outer liner segment portion including an outer liner segment portion radial wall of the annular outer liner radial wall, and the inner liner including an inner liner segment portion radial wall of the annular inner liner radial wall, wherein the outer liner segment portion radial wall includes the plurality of outer liner swirl vanes in the first circumferential zone of the outer liner segment portion radial wall and does not include the plurality of outer liner swirl vanes in the second circumferential zone of the outer liner segment portion radial wall, and the inner liner segment portion radial wall does not include the plurality of inner liner swirl vanes in the first circumferential zone of the inner liner segment portion radial wall and includes the plurality of inner liner swirl vanes on the second circumferential zone of the inner liner segment portion radial wall, the first circumferential zone of the outer liner segment portion radial wall is diametrically opposed to the first circumferential zone of the inner liner segment portion radial wall, and the second circumferential zone of the outer liner segment portion radial wall is diametrically opposed to the second circumferential zone of the inner liner segment portion radial wall.

6. The combustor liner according to claim 5, wherein, wherein the plurality of outer liner swirl vanes in the first circumferential zone of the outer liner segment portion radial wall are configured to provide outer liner segment swirl of oxidant into the combustion chamber in a first circumferential swirl direction about a segment swirler centerline axis of the corresponding segment swirler, the segment swirler centerline axis extending in the axial direction, and the plurality of inner liner swirl vanes in the second circumferential zone of the inner liner segment portion radial wall are configured to provide inner liner segment swirl of oxidant into the combustion chamber in the first circumferential swirl direction.

7. The combustor liner according to claim 6, wherein wherein outer liner radial flow of oxidant is provided through the second circumferential zone of the outer liner segment portion radial wall in the radial direction, and inner liner radial flow of oxidant is provided through the first circumferential zone of the inner liner segment portion radial wall in the radial direction.

8. The combustor liner according to claim 6, wherein, wherein each of the plurality of outer liner swirl vanes disposed in the first circumferential zone of the outer liner segment portion radial wall is arranged at a different circumferential angle relative to the segment swirler centerline axis, and each of the plurality of inner liner swirl vanes disposed in the second circumferential zone of the inner liner segment portion radial wall is arranged at a different circumferential angle relative to the segment swirler centerline axis.

9. The combustor liner of claim 4, wherein wherein the outer liner further includes a second annular outer liner slot dilution opening disposed on an upstream side of the annular outer liner radial wall, and the inner liner further includes a second annular inner liner slot dilution opening disposed on an upstream side of the annular inner liner radial wall.

10. The combustor liner according to claim 9, wherein, wherein the second annular outer liner slot dilution opening includes a second plurality of outer liner swirl vanes, a conical radially inner portion of the plurality of outer liner swirl vanes extending from a downstream side of the annular outer liner slot dilution opening of the outer liner hot surface side to a radially inner end of the annular outer liner radial wall, and a conical radially inner portion of the second plurality of outer liner swirl vanes extending from an upstream side of the outer liner second annular slot dilution opening of the outer liner hot surface side to the radially inner end of the annular outer liner radial wall, and the second annular inner liner slot dilution opening includes a second plurality of inner liner swirl vanes, a conical radially inner portion of the plurality of inner liner swirl vanes extending from a downstream side of the annular inner liner slot dilution opening of the inner liner hot surface side to a radially inner end of the annular inner liner radial wall, and a conical radially inner portion of the second plurality of inner liner swirl vanes extending from an upstream side of the inner liner second annular slot dilution opening of the inner liner hot surface side to the radially inner end of the annular inner liner radial wall. The second annular inner liner slot dilution opening includes a second plurality of inner liner swirl vane blades, wherein a tapered radially outer portion of the plurality of inner liner swirl vane blades extends from a downstream side of the inner liner slot dilution opening on the inner liner hot surface side to a radially outer end of the annular inner liner radial wall, and a tapered radially outer portion of the second plurality of inner liner swirl vane blades extends from an upstream side of the inner liner second annular slot dilution opening on the inner liner hot surface side to the radially outer end of the annular inner liner radial wall.

11. The combustor liner according to claim 9, wherein, wherein, The annular outer liner radial wall further extends into an outer flow passage on the outer liner cold surface side, and the outer liner further includes: (a) a second annular outer liner radial wall disposed on a downstream side of the annular outer liner slot dilution opening and extending radially outward from the outer liner cold surface side into the outer flow passage, the plurality of outer liner swirl vane blades being disposed between the annular outer liner radial wall and the second annular outer liner radial wall; (b) a third annular outer liner radial wall disposed on an upstream side of the second annular outer liner slot dilution opening and extending radially outward from the outer liner cold surface side into the outer flow passage; and (c) a second plurality of outer liner swirl vane blades disposed in the second annular outer liner slot dilution opening between the annular outer liner radial wall and the third annular outer liner radial wall, a trailing edge of each of the plurality of outer liner swirl vane blades being disposed adjacent the outer liner cold surface side, and a trailing edge of each of the second plurality of outer liner swirl vane blades being disposed adjacent the outer liner cold surface side, and The annular inner liner radial wall further extends into an inner flow passage on the inner liner cold surface side, and the inner liner further includes: (a) a second annular inner liner radial wall disposed on a downstream side of the annular inner liner slot dilution opening and extending radially inward from the inner liner cold surface side into the inner flow passage, the plurality of inner liner swirl vane blades being disposed between the annular inner liner radial wall and the second annular inner liner radial wall; (b) a third annular inner liner radial wall disposed on an upstream side of the second annular inner liner slot dilution opening and extending radially inward from the inner liner cold surface side into the inner flow passage; and (c) a second plurality of inner liner swirl vane blades disposed in the second annular inner liner slot dilution opening between the annular inner liner radial wall and the third annular inner liner radial wall, a trailing edge of each of the plurality of inner liner swirl vane blades being disposed adjacent the inner liner cold surface side, and a trailing edge of each of the second plurality of inner liner swirl vane blades being disposed adjacent the inner liner cold surface side.

12. The combustor liner according to claim 9, wherein, wherein, a trailing edge of each of the plurality of outer liner scroll wheel vanes extends from a radially inner end of the annular outer liner radial wall to a downstream side of the annular outer liner slot dilution opening on the outer liner hot surface side of the outer liner, and wherein a trailing edge of each of the plurality of inner liner scroll wheel vanes extends from a radially outer end of the annular inner liner radial wall to a downstream side of the annular inner liner slot dilution opening on the inner liner hot surface side of the inner liner.

13. The combustor liner as in claim 9, wherein, wherein, the outer liner further comprises a second annular outer liner radial wall disposed on a downstream side of the annular outer liner slot dilution opening, the plurality of outer liner scroll wheel vanes are disposed between the annular outer liner radial wall and the second annular outer liner radial wall, and the inner liner further comprises a second annular inner liner radial wall disposed on a downstream side of the annular inner liner slot dilution opening, the plurality of inner liner scroll wheel vanes are disposed between the annular inner liner radial wall and the second annular inner liner radial wall.

14. The combustor liner according to claim 13, wherein, wherein, the outer liner further comprises: (a) a third annular outer liner radial wall disposed on an upstream side of the second annular outer liner slot dilution opening and extending at least partially into an outer flow passage on the outer liner cold surface side; and (b) a second plurality of outer liner scroll wheel vanes disposed in the second annular outer liner slot dilution opening between the third annular outer liner radial wall and the annular outer liner radial wall, the annular outer liner radial wall further extending at least partially into the outer flow passage, and the inner liner further comprises: (a) a third annular inner liner radial wall disposed on an upstream side of the second annular inner liner slot dilution opening and extending at least partially into an inner flow passage on the inner liner cold surface side; and (b) a second plurality of inner liner scroll wheel vanes disposed in the second annular inner liner slot dilution opening between the third annular inner liner radial wall and the annular inner liner radial wall, the annular inner liner radial wall further extending at least partially into the inner flow passage.

15. The combustor liner as in claim 13, wherein, wherein, the annular outer liner radial wall and the second annular outer liner radial wall extend into the combustion chamber at a downstream angle relative to the radial direction, and the annular inner liner radial wall and the second annular inner liner radial wall extend into the combustion chamber at a downstream angle relative to the radial direction.

16. The combustor liner according to claim 15, wherein, wherein, the annular outer liner radial wall and the second annular outer liner radial wall extend into the combustion chamber at a downstream angle relative to the radial direction, and the annular inner liner radial wall and the second annular inner liner radial wall extend into the combustion chamber at a downstream angle relative to the radial direction. The outer liner further includes: (a) a third annular outer liner slot dilution opening disposed downstream of the second annular outer liner radial wall; and (b) a third annular outer liner radial wall disposed downstream of the third annular outer liner slot dilution opening and extending into the combustion chamber at a downstream angle relative to the radial direction; and (c) a second plurality of outer liner swirl vanes disposed in the third annular outer liner slot dilution opening, the third annular outer liner slot dilution opening being arranged between the second annular outer liner radial wall and the third annular outer liner radial wall, and The inner liner further includes: (a) a third annular inner liner slot dilution opening downstream of the second annular inner liner radial wall; and (b) a third annular inner liner radial wall disposed downstream of the third annular inner liner slot dilution opening and extending into the combustion chamber at a downstream angle relative to the radial direction; and (c) a second plurality of inner liner swirl vanes disposed in the third annular inner liner slot dilution opening, the third annular inner liner slot dilution opening being arranged between the second annular inner liner radial wall and the third annular inner liner radial wall.

17. The combustor liner as in claim 13, wherein wherein, The annular outer liner radial wall and the second annular outer liner radial wall extend radially into the combustion chamber perpendicular to the axial direction, and the annular inner liner radial wall and the second annular inner liner radial wall extend radially into the combustion chamber perpendicular to the axial direction.

18. The combustor liner according to claim 17, wherein, wherein, The second annular outer liner slot dilution opening includes a second plurality of outer liner swirl vanes disposed upstream of the annular outer liner radial wall, and the second annular inner liner slot dilution opening includes a second plurality of inner liner swirl vanes disposed upstream of the annular inner liner radial wall.

19. The combustor liner according to claim 17, wherein, wherein, The outer liner further includes: (a) a third annular outer liner slot dilution opening downstream of the second annular outer liner radial wall; (b) a third annular outer liner radial wall disposed downstream of the third annular outer liner slot dilution opening and extending radially into the combustion chamber perpendicular to the axial direction; and (c) a second plurality of outer liner swirl vanes disposed in the third annular outer liner slot dilution opening, the third annular outer liner slot dilution opening being arranged between the second annular outer liner radial wall and the third annular outer liner radial wall, and The inner liner further comprises: (a) a third annular inner liner slot dilution opening downstream of the second annular inner liner radial wall; (b) a third annular inner liner radial wall disposed downstream of the third annular inner liner slot dilution opening and extending radially into the combustion chamber perpendicular to the axial direction; and (c) a second plurality of inner liner swirler vanes disposed in the third annular inner liner slot dilution opening arranged between the second annular inner liner radial wall and the third annular inner liner radial wall.

20. The combustor liner of claim 17, wherein wherein, The annular outer liner radial wall further extends into an outer flow passage of the outer liner cold surface side, and the outer liner further comprises: (a) a third annular outer liner radial wall extending radially outward from the outer liner cold surface side of an upstream side of the second annular outer liner slot dilution opening into the outer flow passage; and (b) a second plurality of outer liner swirler vanes disposed in the second annular outer liner slot dilution opening between the annular outer liner radial wall and the third annular outer liner radial wall, a trailing edge of each of the plurality of outer liner swirler vanes is disposed proximate a radially inner end of the annular outer liner radial wall, and a trailing edge of each of the second plurality of outer liner swirler vanes is disposed proximate the outer liner cold surface side, and The annular inner liner radial wall further extends into an inner flow passage of the inner liner cold surface side, and the inner liner further comprises: (a) a third annular inner liner radial wall extending radially inward from the inner liner cold surface side of an upstream side of the second annular inner liner slot dilution opening into the inner flow passage; and (b) a second plurality of inner liner swirler vanes disposed in the second annular inner liner slot dilution opening between the annular inner liner radial wall and the third annular inner liner radial wall, a trailing edge of each of the plurality of inner liner swirler vanes is disposed proximate a radially outer end of the annular inner liner radial wall, and a trailing edge of each of the second plurality of inner liner swirler vanes is disposed proximate the inner liner cold surface side.

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