Cyclone anti-dilution using shaped cooling grates

Abstract

A combustor liner for a gas turbine combustor includes an outer liner extending circumferentially about a centerline of the combustor and an inner liner extending circumferentially about the centerline of the combustor, wherein the outer liner and the inner liner define a combustion chamber therebetween. At least one of the outer liner and the inner liner includes a dilution flow assembly, the dilution flow assembly comprising: (a) an annular slot dilution opening; and (b) a dilution fence extending from an upstream side of the annular slot dilution opening to a downstream side of the annular slot dilution opening and extending into the combustion chamber, the dilution fence including a plurality of dilution openings therethrough for providing an oxidant flow through the dilution fence and into the combustion chamber.

Description

Technical Field

[0001] The present disclosure relates to dilution of combustion gases in a combustor of a gas turbine engine. Background Art

[0002] In conventional gas turbine engines, it is known to provide a dilution air flow into the combustion chamber downstream of the main combustion zone. Conventionally, an annular combustor liner may include an inner liner and an outer liner that form a combustion chamber therebetween. The inner and outer liners may include dilution holes through the liner that provide an air flow (i.e., a dilution jet) from a passage around the annular combustor liner into the combustion chamber. Some applications are known to use circular holes to provide a dilution air flow to the combustion chamber. The air flow through the circular dilution holes 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., in the wake region of the dilution jet) is associated with high NO x In addition, the circular dilution air jets do not spread laterally, which results in high temperatures between the dilution jets, which also contributes to high NO x form. BRIEF DESCRIPTION OF THE DRAWINGS

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

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

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

[0006] Figure 3 Depicted is a method according to one aspect of the present disclosure Figure 2 A partial cross-sectional view of the dilution flow assembly taken at detailed view 100 of FIG.

[0007] Figure 4 Depicted is another aspect of the present disclosure. Figure 2 A partial cross-sectional view of the dilution flow assembly taken at detailed view 100 of FIG.

[0008] Figure 5 Depicted is a method according to one aspect of the present disclosure Figure 4 A partial cross-sectional rear view of the dilution flow assembly taken at plane 5-5 of FIG.

[0009] Figure 6 Depicted are front and rear partially cutaway perspective views of a combustor according to an aspect of the present disclosure.

[0010] Figure 7 Depicted is a diagram captured at view 101 according to an aspect of the present disclosure. Figure 6 A magnified view of the dilution flow components is shown in FIG.

[0011] Figure 8 According to another aspect of the present disclosure, Figure 2 A partial cross-sectional view of the dilution flow assembly taken at detailed view 100 of FIG.

[0012] Figure 9 Depicted is a method according to one aspect of the present disclosure Figure 2 A partial cross-sectional view of the relationship between the inner liner dilution flow assembly and the outer liner dilution flow assembly taken at detailed view 180 of FIG.

[0013] Figure 10 Another aspect of the present disclosure is described in Figure 2 A partial cross-sectional view of the relationship between the inner liner dilution flow assembly and the outer liner dilution flow assembly taken at detailed view 180 of FIG. DETAILED DESCRIPTION

[0014] Various embodiments are discussed in detail below. Although specific embodiments are discussed, this is for illustrative purposes only. Those skilled in the relevant art will recognize that other components and configurations may be used without departing from the spirit and scope of the present disclosure.

[0015] As used herein, the terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another, and are not intended to indicate the position or importance of each component.

[0016] The terms "upstream" and "downstream" refer to relative directions of fluid flow in a fluid path. For example, "upstream" refers to the direction from which the fluid is flowing, and "downstream" refers to the direction toward which the fluid is flowing.

[0017] In the combustion section of a turbine engine, air flows through outer passages surrounding the combustor liner and through inner passages surrounding the combustor liner. Air generally flows from the upstream end of the combustor liner to the downstream end of the combustor liner. Some of the airflow in the outer and inner passages is diverted through dilution holes in the combustor liner and enters the combustion chamber as dilution air. One purpose of the dilution air flow 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 main zone must be quenched quickly and efficiently so that the high temperature areas can be minimized, thereby reducing NO from the combustion system. x emission.

[0018] The present disclosure aims to reduce NO by improving the dilution quenching of hot combustion gases from the primary combustion zone. x Emissions. According to the present disclosure, a combustor liner includes a dilution flow assembly having a dilution fence extending into a combustion chamber. The dilution fence includes an upstream wall and a downstream wall, and a plurality of dilution openings extending through the upstream wall to provide a dilution air flow into the combustion chamber in a direction opposite to the flow of combustion gases. That is, the dilution openings in the upstream wall of the dilution fence are arranged to provide a dilution air flow in an upstream direction, which is opposite to the flow of combustion gases flowing in a downstream direction. As a result, better mixing of the dilution air with the combustion gases and higher turbulence can be achieved, thereby reducing NO x In addition, the downstream wall may also include a plurality of dilution openings or cooling channels to provide surface cooling for the liner downstream of the dilution fence and also reduce the wake area that may appear at the fence apex within the combustion chamber. By reducing the wake area, NO emissions are further reduced. x emission.

[0019] Referring now to the accompanying drawings, Figure 1 is a schematic partial cross-sectional side view of an exemplary high bypass turbofan jet engine 10 (referred to herein as "engine 10") that may incorporate various embodiments of the present disclosure. Although further described below with reference to a turbofan engine, the present disclosure is also applicable to turbomachinery in general, including turbojets, turboprops, and turboshaft gas turbine engines, including marine and industrial turbine engines and auxiliary power units. Figure 1 As shown, engine 10 has a longitudinal axis or axial centerline axis 12 extending therethrough for reference purposes from an upstream end 98 to a downstream end 99. Generally, engine 10 may include a fan assembly 14 and a core engine 16 disposed downstream of fan assembly 14.

[0020] The core engine 16 may generally include a casing 18 defining an annular inlet 20. The casing 18 surrounds or at least partially forms, in series flow relationship: a compressor section (22 / 24) having a boost or low pressure (LP) compressor 22 and a high pressure (HP) compressor 24; a combustor 26; a turbine section (28 / 30) including a high pressure (HP) turbine 28 and a low pressure (LP) turbine 30; and an ejection exhaust nozzle section 32. A high pressure (HP) rotor shaft 34 drivingly connects the HP turbine 28 to the HP compressor 24. A low pressure (LP) rotor shaft 36 drivingly connects the LP turbine 30 to the LP compressor 22. The LP rotor shaft 36 may also be connected to a fan shaft 38 of the fan assembly 14. In certain embodiments, as shown Figure 1As shown, LP rotor shaft 36 can be connected to fan shaft 38 via reduction gear 40, such as in an indirect drive configuration or a gear drive configuration. In other embodiments, although not shown, engine 10 can also include an intermediate pressure (IP) compressor and a turbine rotatable with the IP shaft.

[0021] like Figure 1 As shown, the fan assembly 14 includes a plurality of fan blades 42 coupled to and extending radially outward from the fan shaft 38. An annular fan casing or nacelle 44 circumferentially surrounds the fan assembly 14 and / or at least a portion of the core engine 16. 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. In addition, at least a portion of the nacelle 44 may extend over an outer portion of the core engine 16 to define a bypass airflow passage 48 therebetween.

[0022] Figure 2 Yes Figure 1 A cross-sectional side view of an exemplary combustor 26 of the core engine 16 is shown. Figure 2 As shown, the combustor 26 may generally define a combustor centerline 111 , which may correspond to the engine axial centerline axis 12 , and, although Figure 2 A cross-sectional view is depicted, but the combustor 26 extends circumferentially about a combustor centerline 111. The combustor 26 includes a combustor liner 50 having an inner liner 52 and an outer liner 54, a shroud 60, and a dome assembly 56. The outer liner 54 and the inner liner 52 extend circumferentially about the combustor centerline 111. The dome assembly 56 extends radially between the outer liner 54 and the inner liner 52 and also extends circumferentially about the combustor centerline 111. The inner liner 52, the outer liner 54, and the dome assembly 56 together define a combustion chamber 62 that extends circumferentially about the combustor centerline 111 and extends from an upstream end 132 to a downstream end 134. The combustion chamber 62 may more specifically define various regions, including a primary combustion zone 71 where an initial chemical reaction of the fuel-oxidant mixture and / or recirculation of the combustion gases 86 may occur before flowing further downstream to the dilution zone 72. In the dilution zone 72, as will be described in more detail below, the combustion gases 86 may flow through the turbine inlet 68 to the HP turbine 28 and the LP turbine 30 ( Figure 1 ) before being mixed with compressed air 82(c).

[0023] like Figure 2As shown, the inner liner 52 can be mounted within the inner shell 65, and the outer liner 54 can be mounted within the outer shell 64. An outer oxidant flow passage 88 is defined between the outer shell 64 and the outer liner 54, and an inner oxidant flow passage 90 is defined between the inner shell 65 and the inner liner 52. The outer liner 54 can include an outer liner dilution flow assembly 92, and the inner liner 52 can include an inner liner dilution flow assembly 94. Both the outer liner dilution flow assembly 92 and the inner liner dilution flow assembly 94 can extend circumferentially around the combustor centerline 111. Various aspects of the outer liner dilution flow assembly 92 and the inner liner dilution flow assembly 94, as well as their relationship within the combustor 26, will be described in greater detail below. Generally, the outer liner dilution flow assembly 92 and the inner liner dilution flow assembly 94 provide a compressed air flow 82(c) therethrough and into the dilution zone 72 of the combustion chamber 62. The compressed air flow 82(c) can therefore be used to provide quenching of the combustion gases 86 in the dilution zone 72, thereby cooling the combustion gas flow 86 entering the turbine section (28 / 30).

[0024] exist Figure 2 In the cross-sectional view of FIG, the combustor 26 is shown to include a swirler assembly 58 and a fuel nozzle assembly 70 connected to the swirler assembly 58. However, as is well known, the combustor 26 includes a plurality of swirler assemblies 58 connected to corresponding openings (not shown) in the dome assembly 56, with the plurality of swirler assemblies 58 circumferentially spaced about the combustor centerline 111. Similarly, a plurality of fuel nozzle assemblies 70 are provided for the corresponding plurality of swirler assemblies 58. Thus, Figure 2 The cross-sectional view depicted in FIG. 1 represents only one of the plurality of swirler assemblies 58 and fuel nozzle assemblies 70 .

[0025] During operation of the engine 10, as Figure 1 and Figure 2 As collectively shown, a quantity of air 73, schematically indicated by arrows, enters engine 10 from upstream end 98 through nacelle 44 and / or associated inlet 76 of fan assembly 14. As quantity of air 73 passes through fan blades 42, a portion of air 73, schematically indicated by arrows 78, is directed or channeled into bypass airflow passage 48, while another portion of air 80, schematically indicated by arrows, is directed or channeled into LP compressor 22. As air 80 flows through LP compressor 22 and HP compressor 24 toward combustor 26, air 80 is progressively compressed.

[0026] refer to Figure 2, the compressed air 82 now flows into the diffuser cavity 84 of the combustor 26 as schematically indicated by the arrows and pressurizes the diffuser cavity 84. A first portion of the compressed air 82(a) as schematically indicated by the arrows flows from the diffuser cavity 84 into the pressure chamber 66 within the shroud 60 and is then swirled through the swirler assembly 58 in the pressure chamber 66 and mixed with the fuel provided by the fuel nozzle assembly 70 to produce a swirling fuel / oxidizer mixture 85 which is then ignited and combusted to produce combustion gases 86. The swirling fuel / oxidizer mixture 85 may swirl around the swirler centerline 95 in a swirler flow direction 97 which may be in a clockwise direction around the swirler centerline 95 or may be in a counterclockwise direction around the swirler centerline 95. The second portion of the compressed air 82 that enters the diffuser cavity 84, as schematically indicated by the arrows, compressed air 82(b), may be used for various purposes other than combustion. For example, Figure 2 As shown, compressed air 82(b) can be directed into the outer oxidant flow passage 88 and the inner oxidant flow passage 90. A portion of the compressed air 82(b) can then be directed from the outer oxidant flow passage 88 through the outer liner dilution flow assembly 92 (schematically shown by arrows as compressed air 82(c)) and into the dilution zone 72 of the combustor 62 to provide quenching of the combustion gases 86 in the dilution zone 72. The compressed air 82(c) can also provide turbulence to the flow of the combustion gases 86, thereby improving mixing of the compressed air 82(c) with the combustion gases 86. Similar flow of the compressed air 82(c) from the inner oxidant flow passage 90 through the liner dilution flow assembly 94 of the liner 52 occurs. Additionally, or alternatively, at least a portion of the compressed air 82(b) can be directed from the diffuser cavity 84 through various flow passages (not shown) to provide cooling air to at least one of the HP turbine 28 or the LP turbine 30.

[0027] Again, common reference Figure 1 and Figure 2 The combustion gases 86 produced in the combustion chamber 62 flow from the combustor 26 into the HP turbine 28, thereby causing the HP rotor shaft 34 to rotate, thereby supporting the operation of the HP compressor 24. Figure 1 As shown, combustion gases 86 are then directed through LP turbine 30, causing LP rotor shaft 36 to rotate, thereby supporting operation of LP compressor 22 and / or rotation of fan shaft 38. Combustion gases 86 are then exhausted through jet exhaust nozzle section 32 of core engine 16 to provide propulsion at downstream end 99.

[0028] Figure 3 is Figure 2 A partial cross-sectional view of the dilution flow assembly is taken at detail view 100 of FIG. Figure 3 The outer liner dilution flow assembly 92 is depicted, but it can be easily understood that Figure 3 The same applies to the liner dilution flow assembly 94, albeit in a mirror image arrangement. Figure 3 Some elements in FIG include corresponding reference numerals in parentheses for corresponding elements of the liner. The outer liner dilution flow assembly 92 extends circumferentially about the combustor centerline 111 and extends Figure 3 10. In the embodiment of the present invention, the outer liner 54 is shown as having an annular slot dilution opening 102 having an upstream side 104 and a downstream side 106. The annular slot dilution opening 102 extends circumferentially through the outer liner 54 about a combustor centerline 111. The outer liner dilution flow assembly 92 also includes a dilution fence 108 that extends from the upstream side 104 of the annular slot dilution opening 102 to the downstream side 106 of the annular slot dilution opening 102. The dilution fence 108 also extends in a radial direction (R) from a hot surface side 110 of the outer liner 54 into the combustion chamber 62. The dilution fence 108 also includes a plurality of dilution openings 112 therethrough for providing an oxidant flow through the dilution fence 108 and into the combustion chamber 62.

[0029] exist Figure 3 6. The dilution fence 108 of FIG. 5 is shown to include an upstream wall 114 extending from the upstream side 104 of the annular slot dilution opening 102 into the combustion chamber 62, and a downstream wall 116 extending from the downstream side 106 of the annular slot dilution opening 102 into the combustion chamber 62. The downstream wall 116 may also include a deflector portion 122 extending from a cold surface side 124 of the outer liner 54 into the outer oxidant flow channel 88. The height 126 of the deflector portion 122 of the downstream wall 116 may vary depending on the amount of oxidant (compressed air 82(b)) to be diverted from the outer oxidant flow channel 88 into the dilution flow channel 120. In addition, an outer portion 128 of the deflector portion 122 may be shaped (e.g., spoon-shaped) to direct the oxidant flow (compressed air 82(b)) into the dilution flow channel 120.

[0030] Figure 3 The dilution fence 108 of the present aspect is further viewed as including an axial connecting wall 118 that extends in the longitudinal direction (L) and connects the upstream wall 114 and the downstream wall 116 within the combustion chamber 62. In other aspects, as described below, the axial connecting wall 118 may be omitted, and the upstream wall 114 and the downstream wall 116 may instead be connected together. Figure 3The dilution flow passage 120 is defined between the annular slot dilution opening 102, the upstream wall 114, the downstream wall 116, and the axial connecting wall 118. The axial connecting wall 118 may include a plurality of dilution jets 130 therethrough, the plurality of dilution jets 130 being spaced circumferentially about the combustor centerline 111. The plurality of dilution jets 130 may provide a radial flow of oxidant (compressed air 82(c)) from the dilution flow passage 120 in a radial direction (R) into the combustion chamber 62. However, the dilution jets 130 may be angled (not shown) to direct the flow of oxidant (compressed air 82(c)) toward the upstream end 132 of the combustion chamber 62 or toward the downstream end 134 of the combustion chamber 62.

[0031] A plurality of dilution openings 112 may be provided through at least one of the upstream wall 114 and the downstream wall 116 ( Figure 3 1 through the downstream wall 116). Alternatively, rather than providing a plurality of dilution openings 112 through the downstream wall 116, a plurality of cooling passages 136 may be provided through the downstream wall 116. The cooling passages 136 provide some of the compressed air 82(b) from the dilution flow passages 120 to flow through the downstream wall, thereby providing cooling to the downstream surface of the downstream wall 116, and provide some cooling air to also flow near the hot surface side 110 of the outer liner 54. Figure 3 In an aspect of the present invention, the plurality of dilution openings 112 may be arranged at an angle 138 relative to the combustor centerline 111 in an upstream direction toward the upstream end 132 . Similarly, the cooling passages 136 may be arranged at an angle 139 in a downstream direction toward the downstream end 134 .

[0032] Now refer to Figures 4 to 7 , another arrangement of dilution openings through the upstream wall 114 will be described. Figure 3 similar, Figure 4 is Figure 2 A partial cross-sectional side view of the liner dilution flow assembly 94 is shown taken at detail view 100 of FIG. Figure 5 is Figure 4 Rear view of a partial cross section taken at plane 5-5 of FIG. Figure 6 yes Figure 2 A front and rear cross-sectional view of a portion of the combustor 26 is shown, Figure 7 is Figure 6 An enlarged perspective view taken at view 101 of FIG. Figures 4 to 7In the aspect of FIG. 1 , a plurality of dilution openings can be seen arranged in a plurality of rows through the upstream wall 114, including a first row 154 of dilution openings 140, a second row 156 of dilution openings 144, and a third row 158 of dilution openings 150. Each of the first row 154, the second row 156, and the third row 158 extends circumferentially about the combustor centerline 111, and each row is radially offset from the other rows. For example, the first row 154 of the plurality of dilution openings 140 is radially offset from the second row 156 of dilution openings 144 by a distance 166, and the second row 156 of dilution openings 144 is radially offset from the third row 158 of dilution openings 150 by a distance 168, where the radial distances are taken relative to the combustor centerline 111. Additionally, as shown in FIG. Figure 7 As generally shown, the dilution openings of one row (eg, the dilution openings 140 of the first row 154 ) may be circumferentially offset from the dilution openings of another row (eg, the dilution openings 144 of the second row 156 ).

[0033] Return Reference Figure 4 , it can be seen that the plurality of dilution openings 140 of the first row 154 are arranged to direct the oxidant flow 230 (compressed air 82(c)) from the dilution flow passage 120 in a first direction 142 to the combustion chamber 62. For example, the dilution openings 140 may be arranged at an angle 160 to provide the oxidant flow 230 (compressed air 82(c)) in the first direction 142 toward the upstream end 132 of the combustion chamber, and as shown Figure 5 As shown, the first direction 142 may be in a radial direction (R) toward the combustor centerline 111. On the other hand, the plurality of dilution openings 144 of the second row 156 may be arranged at an angle 162 to direct the oxidant flow 232 (compressed air 82(a)) from the dilution flow passage 120 into the combustion chamber 62 in a second direction 146 toward the upstream end 132, wherein the angle 162 may be different from the angle 160. Figure 5 , the plurality of dilution openings 144 in the second row 156 may be arranged at an angle 148 relative to the circumferential direction (C) to direct the oxidant flow 232 (compressed air 82(c)) at least partially laterally within the combustion chamber 62. Furthermore, the plurality of dilution openings 150 in the third row 158 may be arranged at an angle 164 to direct the oxidant flow 234 (compressed air 82(a)) from the dilution flow passage 120 into the combustion chamber 62 in a third direction 151 toward the upstream end 132, wherein the angle 164 may be different from the angles 160 and 162. Furthermore, referring to Figure 5, the plurality of dilution openings 150 of the third row 158 may be arranged at an angle 152 relative to the circumferential direction (C) so as to direct the oxidant flow 234 (compressed air 82(c)) at least partially laterally within the combustion chamber 62 in a lateral direction opposite the second direction 146. Thus, with the dilution openings 140 providing the oxidant flow 230 in a first direction 142, the dilution openings 144 providing the oxidant flow 232 in a second direction 146 different from the first direction 142, and the dilution openings 150 providing the oxidant flow 234 in a third direction 151 different from the first direction 142 and the second direction 146, better mixing of the compressed air 82(c) with the combustion gases 86 may be achieved within the combustion chamber 62. Furthermore, by providing the dilution openings 140, 144, and 150 through the upstream wall 114, the oxidant flow 230, 232, 234 passing through each of the dilution openings 140, 144, and 150 is directed toward the combustion chamber 62 (see FIG. 2 ). Figure 2 ), the flows 230, 232, and 234 are in the opposite direction to the downstream flow of the combustion gases 86, thereby providing greater turbulence in the mixing of the combustion gases 86 with the oxidant (compressed air 82(c)). As a result, the wake that might otherwise form at the trailing edge of a conventional dilution hole can be reduced, thereby reducing NOx within the combustor. x Gas emissions.

[0034] Figure 8 Depicted in Figure 2 Another aspect of the outer liner dilution flow assembly 92 is shown in detail view 100 of FIG. Figure 8 In the embodiment of the present invention, the axial connecting wall 118 is omitted, and the upstream wall 114 and the downstream wall 116 are connected to each other. The upstream wall 114 is arranged at an upstream wall angle 170 and extends from the upstream side 104 of the annular slot dilution opening 102 toward the downstream end 134 and into the combustion chamber 62. The upstream wall angle 170 may range from ten degrees to one hundred and sixty degrees. Of course, other angles may be used instead. The downstream wall 116 extends from the downstream side 106 of the annular slot dilution opening 102 toward the upstream end 132 and into the combustion chamber 62 at a downstream wall angle 172. The downstream wall angle 172 may range from ten degrees to one hundred and sixty degrees, but of course, other angles may be used instead. The upstream wall 114 and the downstream wall 116 define an apex 174 at the connection between the upstream wall 114 and the downstream wall 116 within the combustion chamber 62. The upstream wall 114 and the downstream wall 116 may be connected together by, for example, brazing or welding together to define the apex 174. Alternatively, the upstream wall 114 and the downstream wall 116 may be integrally formed with one another, for example, by additive manufacturing or by forming through known metal forming processes. Figure 3 In terms of Figure 8The upstream wall 114 in the embodiment includes a plurality of dilution openings 112, which may be arranged at an angle 138. Figure 8 108. In another embodiment, the downstream wall 116 is shown as including a plurality of downstream wall dilution openings 176 therethrough. The downstream wall dilution openings 176 may be arranged at an angle 178 in a downstream direction toward the downstream end 134. While the dilution openings 112 through the upstream wall 114 may provide increased mixing of the compressed air 82(c) with the combustion gases 86 in the primary combustion zone 71, the compressed air 82(c) through the downstream wall dilution openings 176 may provide mixing downstream of the dilution fence 108 and also help shape the combustor exit temperature profile.

[0035] Figure 9 Depicted in Figure 2 A partial cross-sectional view taken at detail view 180 of FIG. Figure 9 The relationship between the dilution fence 108 of the outer liner dilution flow assembly 92 and the dilution fence 182 of the inner liner dilution flow assembly 94 will be described. The dilution fence 182 is similar to the above Figure 8 The dilution fence 108 is depicted and may be a mirror image of the dilution fence 108. Thus, the dilution fence 182 may extend from the upstream side 183 of the annular slot dilution opening 188 to the downstream side 185 of the annular slot dilution opening 188. However, in Figure 9 , the downstream wall 116 omits the downstream wall dilution opening 176. Instead, the downstream wall 116 may include the cooling passage 136. The dilution fence 182 includes an upstream wall 184 and a downstream wall 186 similar to the upstream wall 114. The upstream wall 184 and the downstream wall 186 are connected together to form an apex 190 similar to the apex 174. The annular slot dilution opening 188 is similar to the annular slot dilution opening 102 and extends through the liner 52. Similar to Figure 3 and 4 A dilution flow passage 187 of the dilution flow passage 120 is formed between the upstream wall 184, the downstream wall 186, and the annular slot dilution opening 188. The upstream wall 184 includes a plurality of dilution openings 192 extending therethrough, similar to the plurality of dilution openings 112 of the upstream wall 114. The downstream wall 186 may include a plurality of cooling passages 137, which may be similar to the cooling passages 136 extending through the downstream wall 116. Like the outer liner 54, the inner liner 52 includes a hot surface side 200 and a cold surface side 201.

[0036] The outer liner dilution flow assembly 92 may be offset in the longitudinal direction (L) relative to the inner liner dilution flow assembly 94. For example, the apex 174 of the outer liner dilution flow assembly 92 and the apex 190 of the inner liner dilution flow assembly 94 may be offset relative to each other in the longitudinal direction (L) by an offset distance 194. The offset distance 194 may be offset relative to the combustor length 204 ( Figure 2) can be in the range of zero to thirty percent of the combustor length 204. Of course, when the offset distance 194 is zero percent of the combustor length 204, the apex 174 and the apex 190 are radially aligned with each other. The apex 174 can be positioned at a height 196 from the hot surface side 110 of the outer liner 54. The height 196 can range from ten percent to forty-five percent of the height 198 of the combustion chamber 62 taken between the hot surface side 110 of the outer liner 54 at the annular slot dilution opening 102 and the hot surface side 200 of the inner liner 52 at the annular dilution opening 188. The height 202 of the apex 190 can similarly be taken as a percentage of the height 198 relative to the hot surface side 200 of the inner liner 52 and can similarly range from ten to forty-five percent of the height 198. The radial distance 206 between the apex 174 and the apex 190 can range from zero to forty percent of the height 198. Of course, when the radial distance 206 is zero percent of the height 198, the apex 174 and the apex 190 will need to have a greater offset distance 194 in order to provide the dilution region 72 ( Figure 2 ) to ensure proper flow of the combustion gases 86 downstream. The radial distance 206 is not limited to the above ranges, and other distance values ​​can be achieved.

[0037] exist Figure 9 In, with Figure 3 Similarly, the plurality of dilution openings 112 through the upstream wall 114 of the outer liner dilution flow assembly 92 are arranged to direct the oxidant flow 226 (i.e., compressed air 82(c)) toward the upstream end 132 at an angle 138. Similarly, the plurality of dilution openings 192 through the upstream wall 184 of the inner liner dilution flow assembly 94 are arranged to direct the oxidant flow 228 (i.e., compressed air 82(c)) toward the upstream end 132 at an angle 208. Thus, a converging flow angle 210 is defined between angle 138 and angle 208. The converging flow angle 210 may range from fifty degrees to one hundred and eighty degrees. Of course, the converging flow angle 210 is not limited to the aforementioned range, and other angle values ​​may also be employed.

[0038] Figure 10 Another arrangement of a dilution flow assembly according to another aspect of the present disclosure is depicted. Figure 10 The arrangement depicted in Figure 9 The arrangement shown in , however, as Figure 10As shown in FIG, a second plurality of liner dilution openings 212 are provided through the outer liner 54 downstream of the downstream wall 116 of the liner dilution flow assembly 92, and a second plurality of liner dilution openings 214 are provided through the inner liner 52 downstream of the downstream wall 186 of the inner liner dilution flow assembly 94. The second plurality of liner dilution openings 212 may be arranged at the downstream wall corner 172 of the downstream wall 116 so that the oxidant flow 216 passing through the second plurality of liner dilution openings 212 flows against the downstream side 218 of the downstream wall 116 to provide surface cooling of the downstream wall 116. In addition, the oxidant flow 216 collides with the combustion gas flow 86 at the apex 174 to reduce the wake that may appear on the downstream side of the apex 174, thereby reducing NO that may otherwise appear in the wake. x Similarly, the second plurality of liner dilution openings 214 may be arranged at a downstream wall corner 224 of the downstream wall 186 such that the oxidant flow 220 passing through the second plurality of liner dilution openings 214 flows against a downstream side 222 of the downstream wall 186 to provide surface cooling of the downstream wall 186. Additionally, the oxidant flow 220 collides with the combustion gas flow 86 at the apex 190 to reduce a wake that may appear on the downstream side of the apex 190, thereby reducing NOx that may otherwise appear in the wake. x emission.

[0039] As described above, the plurality of dilution openings 112 may be arranged at the angle 138 to provide the oxidant flow 226 in an upstream direction toward the upstream end 132 of the combustion chamber 62, and the plurality of dilution openings 192 may be arranged at the angle 208 to provide the oxidant flow 228 in an upstream direction toward the upstream end 132 of the combustion chamber 62. Thus, the angle 138 may be arranged to provide the flow 226 to align with the swirler assembly 58 ( Figure 2 ) of the fuel / oxidant mixture 85, and the angle 208 may be arranged to provide a flow 228 opposite to the flow direction 229 of the swirling fuel / oxidant mixture 85 from the swirler assembly 58. However, the plurality of dilution openings 112 and the plurality of dilution openings 192 may also be arranged at a circumferential angle (not shown) to provide the oxidant flow 226 and the oxidant flow 228 in a circumferential direction relative to the swirler centerline 95. For example, the plurality of dilution openings 112 and the plurality of dilution openings 192 may include a circumferential angle, such as described above with respect to the plurality of dilution openings 112 and the plurality of dilution openings 192. Figure 5 The oxidant flow 232 provided by the plurality of dilution openings 144 in the second row 156 of Figure 51 and 2. The oxidant flow 234 provided by the plurality of dilution openings 150 is depicted in FIG. As described above, the swirling fuel / oxidant mixture 85 injected into the combustion chamber 62 may be swirled about the swirler centerline 95 in the swirler flow direction 97. Accordingly, some of the plurality of dilution openings 112 disposed through the upstream wall 114 and circumferentially opposite the swirler assembly 58 may be disposed to include a circumferential angular component such that the flows 226 and 228 may be co-directional with the swirler flow direction 97 or counter-directional with the swirler flow direction 97.

[0040] While the foregoing description generally relates to gas turbine engines, it will be readily understood that gas turbine engines may be implemented in a variety of environments. For example, the engine may be implemented in an aircraft, but may also be implemented in non-aircraft applications, such as power plants, marine applications, or oil and gas production applications. Therefore, the present disclosure is not limited to use in aircraft.

[0041] Further aspects of the disclosure are provided by the subject matter of the following clauses.

[0042] A combustor liner for a combustor of a gas turbine, the combustor liner comprising: an outer liner extending circumferentially around a combustor centerline; and an inner liner extending circumferentially around the combustor centerline, wherein the outer liner and the inner liner define a combustion chamber therebetween, and at least one of the outer liner and the inner liner comprises a dilution flow assembly, the dilution flow assembly comprising: (a) an annular slot dilution opening; and (b) a dilution fence extending between an upstream side of the annular slot dilution opening to a downstream side of the annular slot dilution opening and extending into the combustion chamber, the dilution fence including a plurality of dilution openings therethrough for providing an oxidant flow through the dilution fence into the combustion chamber.

[0043] The combustor liner of any preceding clause, wherein the dilution fence comprises (i) an upstream wall extending from the upstream side of the annular slot dilution opening into the combustion chamber and (ii) a downstream wall extending from the downstream side of the annular slot dilution opening into the combustion chamber.

[0044] A combustor liner according to any preceding clause, wherein the outer liner and the inner liner define a hot surface side adjacent to the combustion chamber and a cold surface side adjacent to the oxidant flow channel, and the downstream wall includes a deflector portion extending from the cold surface side into the oxidant flow channel.

[0045] The combustor liner of any preceding clause, wherein the upstream wall and the downstream wall are connected within the combustion chamber, a dilution flow path defined between the annular slot dilution opening, the upstream wall, and the downstream wall.

[0046] The combustor liner of any preceding clause, wherein the dilution fence further comprises (iii) an axial connecting wall, wherein the upstream wall and the downstream wall are connected to the axial connecting wall within the combustion chamber, the dilution flow channel being defined between the annular slot dilution opening, the upstream wall, the downstream wall, and the axial connecting wall.

[0047] The combustor liner of any preceding clause, wherein the axial connecting wall includes a plurality of dilution jets therethrough, the plurality of dilution jets providing radial flow of oxidant from the dilution flow channel to the combustion chamber.

[0048] The combustor liner of any preceding clause, wherein the plurality of dilution openings are provided through at least one of the upstream wall and the downstream wall.

[0049] The combustor liner of any preceding clause, wherein the plurality of dilution openings are provided through the upstream wall and a plurality of cooling passages are provided through the downstream wall.

[0050] A combustor liner according to any preceding clause, wherein the plurality of dilution openings are provided through the upstream wall and arranged to direct oxidant flow from the dilution flow channel through the upstream wall and into the combustion chamber at an angle in an upstream direction relative to the combustor centerline.

[0051] The combustor liner of any preceding clause, wherein both the outer liner and the inner liner include the dilution flow assembly, and the angle in the upstream direction of the oxidant flow through the plurality of dilution openings of the outer liner and the angle in the upstream direction of the oxidant flow through the plurality of dilution openings of the inner liner are arranged to converge with each other upstream of the dilution flow assembly.

[0052] The combustor liner of any preceding clause, wherein the plurality of dilution openings of the outer liner and the plurality of dilution openings of the inner liner are arranged to provide oxidant flow in the upstream direction to oppose the flow of the swirling fuel / oxidant mixture injected into the combustion chamber by the swirler assembly.

[0053] The combustor liner of any preceding clause, wherein the plurality of dilution openings are arranged through the upstream wall in a plurality of rows of dilution openings, each row of dilution openings extending circumferentially about the combustor centerline, and wherein a first row of the plurality of dilution openings and a second row of the plurality of dilution openings are arranged radially offset from one another relative to the combustor centerline.

[0054] The combustor liner of any preceding clause, wherein the plurality of dilution openings of the first row are arranged to direct the oxidant flow from the dilution flow channel into the combustion chamber in a first upstream direction, and the plurality of dilution openings of the second row are arranged to direct the oxidant flow from the dilution flow channel into the combustion chamber in a second upstream direction different from the first upstream direction.

[0055] A combustor liner according to any preceding clause, wherein the upstream wall is arranged at an upstream wall angle and extends in a downstream direction into the combustion chamber, and the downstream wall is arranged at a downstream wall angle and extends in an upstream direction into the combustion chamber, the upstream wall and the downstream wall defining an apex within the combustion chamber at a connection between the upstream wall and the downstream wall.

[0056] The combustor liner of any preceding clause, wherein the upstream wall angle has a range from ten degrees to one hundred sixty degrees, and the downstream wall angle has a range from ten degrees to one hundred sixty degrees.

[0057] The combustor liner of any preceding clause, wherein the height of the apex ranges from ten percent to forty-five percent of the distance between the annular slot dilution opening at the hot surface side of the outer liner and the annular slot dilution opening at the hot surface side of the inner liner.

[0058] The combustor liner of any preceding clause, wherein both the outer liner and the inner liner include the dilution flow assembly, the dilution flow assembly of the outer liner being an outer liner dilution flow assembly, and the dilution flow assembly of the inner liner being an inner liner dilution flow assembly.

[0059] The combustor liner of any preceding clause, wherein the apex of the outer liner dilution flow assembly and the apex of the inner liner dilution flow assembly are offset relative to each other in a longitudinal direction.

[0060] The combustor liner of any preceding clause, wherein the plurality of dilution openings through the upstream wall of the outer liner dilution flow assembly are arranged to direct the oxidant flow in the upstream direction at a first angle, and the plurality of dilution openings through the upstream wall of the inner liner dilution flow assembly are arranged to direct the oxidant flow in the upstream direction at a second angle, a converging flow angle defined between the first angle and the second angle, the converging flow angle having a range from fifty degrees to one hundred and eighty degrees.

[0061] The combustor liner of any preceding clause, wherein a radial distance between the apex of the outer liner dilution flow assembly and the apex of the inner liner dilution flow assembly ranges from zero percent to forty percent of a radial distance between the annular slot dilution opening at the hot surface side of the outer liner and the annular slot dilution opening at the hot surface side of the inner liner.

[0062] Although the foregoing description is directed to some exemplary embodiments of the present disclosure, it should be noted that other changes and modifications will be apparent to those skilled in the art and may be made without departing from the spirit or scope of the present disclosure. In addition, features described in conjunction with one embodiment of the present disclosure may be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A combustor liner for a gas turbine combustor, characterized in that: The combustor liner comprises: an outer liner extending circumferentially about a combustor centerline; and a liner extending circumferentially around a centerline of the combustor; wherein the outer liner and the inner liner define a combustion chamber therebetween, and At least one of the outer liner and the inner liner includes a dilution flow assembly, the dilution flow assembly comprising: (a) an annular slot dilution opening; and (b) a dilution fence extending from an upstream side of the annular slot dilution opening to a downstream side of the annular slot dilution opening and extending into the combustion chamber, the dilution fence including a plurality of dilution openings therethrough for providing an oxidant flow through the dilution fence into the combustion chamber; wherein the dilution fence includes (i) an upstream wall extending from the upstream side of the annular slot dilution opening into the combustion chamber and (ii) a downstream wall extending from the downstream side of the annular slot dilution opening into the combustion chamber; wherein the outer liner and the inner liner define a hot surface side adjacent to the combustion chamber and a cold surface side adjacent to the oxidant flow channel, and the downstream wall includes a deflector portion extending from the cold surface side into the oxidant flow channel.

2. The combustor liner according to claim 1, characterized in that The upstream wall and the downstream wall are connected in the combustion chamber, and a dilution flow channel is defined between the annular groove dilution opening, the upstream wall, and the downstream wall.

3. The combustor liner according to claim 2, characterized in that The dilution fence further includes (iii) an axial connecting wall, wherein the upstream wall and the downstream wall are connected to the axial connecting wall within the combustion chamber, and the dilution flow channel is defined between the annular groove dilution opening, the upstream wall, the downstream wall and the axial connecting wall.

4. The combustor liner according to claim 3, characterized in that The axial connecting wall includes a plurality of dilution injection portions therethrough, the plurality of dilution injection portions providing a radial flow of oxidant from the dilution flow channel to the combustion chamber.

5. The combustor liner according to claim 2, wherein: The plurality of dilution openings are provided through at least one of the upstream wall and the downstream wall.

6. The combustor liner according to claim 5, characterized in that The plurality of dilution openings are provided through the upstream wall, and the plurality of cooling channels are provided through the downstream wall.

7. The combustor liner according to claim 5, characterized in that The plurality of dilution openings are provided through the upstream wall and are arranged to direct the oxidant flow from the dilution flow channel through the upstream wall into the combustion chamber at an angle in an upstream direction relative to a centerline of the combustor.

8. The combustor liner according to claim 7, characterized in that wherein both the outer liner and the inner liner include the dilution flow assembly, and the angle in the upstream direction of the oxidant flow through the plurality of dilution openings of the outer liner and the angle in the upstream direction of the oxidant flow through the plurality of dilution openings of the inner liner are arranged to converge with each other upstream of the dilution flow assembly.

9. The combustor liner according to claim 8, characterized in that The plurality of dilution openings of the outer liner and the plurality of dilution openings of the inner liner are arranged to provide an oxidant flow in the upstream direction to oppose a flow of a swirling fuel / oxidant mixture injected into the combustion chamber through a swirler assembly.

10. The combustor liner according to claim 5, wherein The plurality of dilution openings are arranged through the upstream wall in a plurality of rows of dilution openings, each row of dilution openings extending circumferentially around the combustor centerline, and a first row of the plurality of dilution openings and a second row of the plurality of dilution openings are arranged radially offset from each other relative to the combustor centerline.

11. The combustor liner according to claim 10, wherein: wherein the plurality of dilution openings in the first row are arranged to direct the oxidant flow from the dilution flow channel into the combustion chamber in a first upstream direction, and the plurality of dilution openings in the second row are arranged to direct the oxidant flow from the dilution flow channel into the combustion chamber in a second upstream direction different from the first upstream direction.

12. The combustor liner according to claim 1, wherein wherein the upstream wall is arranged at an upstream wall angle and extends into the combustion chamber in a downstream direction, and the downstream wall is arranged at a downstream wall angle and extends into the combustion chamber in an upstream direction, the upstream wall and the downstream wall defining a vertex at a connection between the upstream wall and the downstream wall within the combustion chamber.

13. The combustor liner according to claim 12, wherein: Wherein the upstream wall angle has a range from ten degrees to one hundred and sixty degrees, and the downstream wall angle has a range from ten degrees to one hundred and sixty degrees.

14. The combustor liner according to claim 12, wherein: The height of the apex ranges from ten percent to forty-five percent of the distance between the annular slot dilution opening at the hot surface side of the outer liner and the annular slot dilution opening at the hot surface side of the inner liner.

15. The combustor liner according to claim 12, wherein Wherein both the outer liner and the inner liner include the dilution flow assembly, the dilution flow assembly of the outer liner is an outer liner dilution flow assembly, and the dilution flow assembly of the inner liner is an inner liner dilution flow assembly.

16. The combustor liner according to claim 15, wherein The apex of the outer liner dilution flow assembly and the apex of the inner liner dilution flow assembly are offset relative to each other in a longitudinal direction.

17. The combustor liner according to claim 15, wherein wherein the plurality of dilution openings through the upstream wall of the outer liner dilution flow assembly are arranged to direct the oxidant flow in the upstream direction at a first angle, and the plurality of dilution openings through the upstream wall of the inner liner dilution flow assembly are arranged to direct the oxidant flow in the upstream direction at a second angle, a converging flow angle being defined between the first angle and the second angle, the converging flow angle having a range from fifty degrees to one hundred and eighty degrees.

18. The combustor liner of claim 15, wherein: wherein a radial distance between the apex of the outer liner dilution flow assembly and the apex of the inner liner dilution flow assembly ranges from zero percent to forty percent of a radial distance between the annular slot dilution opening at the hot surface side of the outer liner and the annular slot dilution opening at the hot surface side of the inner liner.

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