Combustor liner with cooling dispersion members for local liner cooling

Abstract

A combustor liner for a gas turbine having a cold side liner section and a hot side liner section with a dam cavity therebetween. At least one cooling airflow dispersion member is disposed within the dam cavity. The at least one cooling airflow dispersion member includes a main cavity portion and at least one peripheral cavity portion surrounding the main cavity portion. The main cavity portion includes a main cavity inlet side having cooling airflow openings, a main cavity outlet side having a plurality of hot side cooling airflow openings, and at least one peripheral cavity outlet flow passage providing fluid communication between the main cavity portion and the at least one peripheral cavity portion. The at least one peripheral cavity portion includes a peripheral cavity outlet side having a plurality of hot side cooling airflow openings.

Description

TECHNICAL FIELD

[0001] The present disclosure relates to a combustor liner having cooling dispersion members for locally cooling the combustor liner. BACKGROUND

[0002] Some gas turbine engines include a multi-layer combustor liner that includes an outer shell and an inner liner with a cooling airflow space between the outer shell and the inner liner. The cooling airflow space typically extends around the entire inner liner. Cooling holes are provided in the outer shell to allow cooling air to flow into the cooling airflow space to provide impingement cooling to the cold side of the inner liner. Cooling holes through the inner liner can also be included to allow some cooling air to flow through the inner liner from the cooling airflow passage to provide surface cooling to the hot side of the inner liner. During operation of the engine, a swirler assembly injects a fuel-air mixture into a combustion chamber where the fuel-air mixture is ignited and burned to generate combustion products. Hot spots can occur on the inner liner closest to the swirler assembly as a result of the combustion. BRIEF DESCRIPTION OF DRAWINGS

[0003] The features and advantages of the present disclosure will be apparent from the following detailed description of various exemplary embodiments, as illustrated in the accompanying drawings, in which like reference numerals generally represent like elements, and in which:

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

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

[0006] Figure 3 is a schematic partial cross-sectional view of a portion of an outer liner in Figure 2 in accordance with aspects of the present disclosure taken at detail view 100.

[0007] Figure 4 is a schematic partial cross-sectional view of a cooling airflow dispersion member 118 taken at plane 4-4 of Figure 3 in accordance with aspects of the present disclosure.

[0008] Figure 5 is a schematic view depicting examples of respective shapes of a primary cavity wall, a first peripheral cavity wall, and a second peripheral cavity wall in accordance with aspects of the present disclosure.

[0009] Figure 6 is a schematic view depicting examples of respective shapes of a primary cavity wall, a first peripheral cavity wall, and a second peripheral cavity wall in accordance with another aspect of the present disclosure.

[0010] Figure 7 is a schematic diagram depicting examples of respective shapes of a primary lumen wall, a first peripheral lumen wall, and a second peripheral lumen wall according to another aspect of the present disclosure.

[0011] Figure 8 is a schematic diagram depicting examples of respective shapes of a primary lumen wall, a first peripheral lumen wall, and a second peripheral lumen wall according to another aspect of the present disclosure.

[0012] Figure 9 is a schematic partial cross-sectional view of a portion of an outer liner taken at detailed view 100 in Figure 2 is a schematic partial cross-sectional view of a portion of an outer liner taken at detailed view 100 in

[0013] Figure 10 is a schematic partial cross-sectional view of a cooling gas flow dispersion member taken at plane 10-10 in Figure 9 is a schematic partial cross-sectional view of a cooling gas flow dispersion member taken at plane 10-10 in

[0014] Figure 11 is a schematic partial cross-sectional view of a portion of an outer liner taken at detailed view 100 in Figure 2 is a schematic partial cross-sectional view of a portion of an outer liner taken at detailed view 100 in

[0015] Figure 12 is a schematic partial cross-sectional view of a portion of an outer liner taken at detailed view 100 in Figure 2 is a schematic partial cross-sectional view of a portion of an outer liner taken at detailed view 100 in

[0016] Figure 13 is a partial cross-sectional view of a cooling gas flow dispersion member taken at plane 13-13 in Figure 12 is a partial cross-sectional view of a cooling gas flow dispersion member taken at plane 13-13 in DETAILED DESCRIPTION

[0017] The features, advantages, and embodiments of the present disclosure are set forth with particularity in the detailed description, the drawings, and the claims that follow. Moreover, it should be noted that the detailed description is intended for purposes of illustration only and is not intended to limit the scope of the present disclosure.

[0018] Various embodiments are discussed in detail below. Although certain embodiments are discussed, this is merely for illustration and other components and configurations can be used without departing from the spirit and scope of the present disclosure.

[0019] As used herein, the terms "first," "second," and "third" can be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components.

[0020] The terms "upstream" and "downstream" refer to the relative direction with respect to the flow of fluid in a fluid path. For example, "upstream" refers to the direction from which fluid flows, and "downstream" refers to the direction to which fluid flows.

[0021] Some gas turbine engines include a multi-layer combustor liner that includes an outer shell and an inner liner with a cooling airflow space between the outer shell and the inner liner. Cooling holes are provided in the shell to allow cooling air to flow into the cooling airflow space to provide impingement cooling to the cold side of the inner liner. Cooling holes can also be included through the inner liner to allow some of the cooling air to flow through the inner liner from the cooling airflow passage to provide surface cooling to the hot side of the inner liner. During operation of the engine, a swirler assembly injects a fuel-air mixture into a combustion chamber where the fuel-air mixture is ignited and burned to generate combustion products. The cooling airflow within the cooling airflow space provides some cooling of the inner liner via impingement of the cooling airflow against the cold side of the inner liner. The portion of the inner liner closest to the ignited fuel-air mixture is subjected to intense heat, which can cause hot spots in the inner liner. Over time, the intense heat in the hot spots can degrade the inner liner such that the inner liner can experience cracking or even possibly have a burn-through hole in the inner liner. While the cooling air flowing within the cooling airflow passage can provide some impingement cooling to the inner liner, the hot spots are still subjected to higher temperatures than other portions of the inner liner.

[0022] The present disclosure provides techniques for locally cooling hot spots of an inner liner. In accordance with the present disclosure, at least one cooling airflow member is provided within the cooling airflow space (i.e., baffle cavity) between the outer shell and the inner liner at an expected hot spot location of the inner liner. The cooling airflow member includes a primary cavity arranged at a highest temperature region of the hot spot of the inner liner, and the primary cavity directs cooling airflow to impinge against the cold side of the inner liner to provide local cooling at the hot spot location. The primary cavity is surrounded by a peripheral cavity, with some of the cooling airflow from the primary cavity flowing into the adjacent peripheral cavity to provide local impingement cooling to the region of the inner liner surrounding the highest temperature region. Additional peripheral cavities can also be included, with cooling airflow provided from an innermost peripheral cavity to the additional peripheral cavities. Each of the primary cavity and the peripheral cavities can also include cooling holes through the inner liner to provide surface cooling on the hot side of the inner liner. Thus, more targeted cooling can be provided at each hot spot of the inner liner, thereby better reducing the temperature at the hot spot and thereby improving the durability of the inner liner.

[0023] Reference will now be made to the drawings, Figure 1is a schematic partial cross-sectional side view of an exemplary high-bypass turbofan jet engine 10 (referred to herein as "engine 10") that can incorporate various embodiments of the present disclosure. Although described further below with reference to a turbofan engine, the present disclosure is also applicable to general turbomachinery, including turbojet engines, turboprop engines, and turboshaft gas turbine engines, including marine turbine engines, industrial turbine engines, and auxiliary power units. As shown, Figure 1 Engine 10 has an axial centerline axis 12 extending therethrough from an upstream end 98 to a downstream end 99 for reference purposes. Generally, engine 10 can include a fan assembly 14 and a core engine 16 disposed downstream of fan assembly 14.

[0024] Core engine 16 can generally include a casing 18 that defines an annular inlet 20. Casing 18 surrounds or at least partially forms, in serial flow relationship: a compressor section (22 / 24) having a low pressure (LP) compressor 22 and a high pressure (HP) compressor 24; a combustor 26; a turbine section (28 / 30) including a high pressure (HP) turbine 28 and a low pressure (LP) turbine 30; and a jet exhaust nozzle section 32. A high pressure (HP) rotor shaft 34 drivingly connects HP turbine 28 to HP compressor 24. A low pressure (LP) rotor shaft 36 drivingly connects LP turbine 30 to LP compressor 22. LP rotor shaft 36 can also be connected to a fan shaft 38 of fan assembly 14. In certain embodiments, as Figure 1 shown, for example, in an indirect drive or geared drive configuration, LP rotor shaft 36 can be connected to fan shaft 38 through a reduction gear 40.

[0025] As Figure 1 shown, fan assembly 14 includes a plurality of fan blades 42 coupled to and extending radially outward from fan shaft 38. An annular fan casing or nacelle 44 circumferentially surrounds at least a portion of fan assembly 14 and / or core engine 16. Nacelle 44 can be supported relative to core engine 16 by a plurality of circumferentially spaced outlet guide vane or struts 46. Further, at least a portion of nacelle 44 can extend over an outer portion of core engine 16 so as to define a bypass airflow passage 48 therebetween.

[0026] Figure 2 is a cross-sectional side view of an exemplary combustor 26 of core engine 16 as Figure 1 shown. As Figure 2As shown, combustor 26 can generally include a combustor liner 50 having an inner liner 52 and an outer liner 54, and a dome assembly 56, which together define a combustion chamber 62. Inner liner 52 and outer liner 54 can both extend circumferentially about a combustor centerline axis 112, which can correspond to engine axial centerline axis 12. Inner liner 52 and outer liner 54 are connected to a cowl 60, and a pressure plenum 66 is defined between cowl 60, inner liner 52, outer liner 54, and dome assembly 56. Combustor 26 also includes a mixer assembly 58 connected to a fuel nozzle assembly 70. While Figure 2 A single mixer assembly 58 and a single fuel nozzle assembly 70 are depicted, but multiple mixer assemblies 58 and corresponding fuel nozzle assemblies 70 can be included in combustor 26, with each respective mixer assembly 58 and fuel nozzle assembly 70 circumferentially spaced about combustor centerline axis 112.

[0027] As Figure 2 shown, inner liner 52 is enclosed within an inner shell 65, while outer liner 54 is enclosed within an outer shell 64. An outer flow passage 88 is defined between outer liner 54 and outer shell 64, while an inner flow passage 90 is defined between inner liner 52 and inner shell 65. Both outer shell 64 and inner shell 65 can extend circumferentially about combustor centerline axis 112. A cold surface side 53 of inner liner 52 is adjacent to inner flow passage 90, while a hot surface side 55 of inner liner 52 is adjacent to combustion chamber 62. Similarly, a cold surface side 57 of outer liner 54 is adjacent to outer flow passage 88, while a hot surface side 59 of outer liner 54 is adjacent to combustion chamber 62. Inner liner 52 and outer liner 54 can extend from dome assembly 56 to turbine nozzles 79 at an inlet of HP turbine 28 Figure 1 ), thus at least partially defining a hot gas path between combustor liner 50 and HP turbine 28. Combustion chamber 62 can more particularly define a primary combustion zone 74 at which an initial chemical reaction of a fuel-oxidant mixture 72 occurs to produce combustion gases 86, and / or at which recirculation of combustion gases 86 can occur before combustion gases 86 flow further downstream to a dilution zone 75. At dilution zone 75, combustion gases 86 are mixed with dilution air before flowing to a secondary combustion zone 77 and into turbine nozzles 79 at an inlet of HP turbine 28 and LP turbine 30. As will be described in greater detail below, both outer liner 54 and inner liner 52 include cooling airflow openings that provide a flow of cooling air from outer flow passage 88 and inner flow passage 90 through outer liner 54 and inner liner 52 to provide cooling to outer liner 54 and inner liner 52. More particularly, each of outer liner 54 and inner liner 52 can have a hot spot 68 where the temperature of the liner is most intense, and as will be described below, the present disclosure provides techniques for better localized cooling at hot spots 68 of outer liner 54 and inner liner 52.

[0028] During operation of the engine 10, as Figure 1 and Figure 2 collectively shown, a volume of air (as schematically indicated by arrow 73) Figure 1 enters the engine 10 from the upstream end 98 through the nacelle 44 and / or an associated nacelle inlet 76 of the fan assembly 14. As the air 73 passes through the fan blades 42, a portion of the air 73 is directed or channeled into the bypass airflow passage 48 as bypass airflow 78, while another portion of the air 73 is directed or channeled into the LP compressor 22 as compressor inlet air 80. The compressor inlet air 80 is progressively compressed as it flows through the LP compressor 22 and the HP compressor 24 toward the combustor 26. As Figure 2 shown, the compressed air 82 flows into 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 plenum chamber 66, where the first portion of the compressed air 82 is mixed with fuel provided by the fuel nozzle assembly 70 by the mixer assembly 58. The fuel-oxidant mixture 72 is then injected into the combustion chamber 62 by the mixer assembly 58. The fuel-oxidant mixture 72 is ignited and combusted to produce combustion gases 86 within the primary combustion zone 74 of the combustion chamber 62. Typically, the LP compressor 22 and the HP compressor 24 provide more compressed air 82 to the diffuser cavity 84 than is needed for combustion. Accordingly, a second portion of the compressed air 82 (as schematically indicated by arrow 82(b)) can be used for various purposes other than combustion. For example, as Figure 2 shown, the compressed air 82(b) can be channeled into the outer flow passage 88 and generally flows downstream in the flow direction 85 within the outer flow passage 88. Similarly, a portion of the compressed air 82(b) can be channeled into the inner flow passage 90 and generally flows downstream in the flow direction 87 within the inner flow passage 90. As will be described in greater detail below, a portion of the compressed air 82(b) can be used to provide cooling for the outer liner 54 and the inner liner 52. In addition, a portion of the compressed air 82(b) can be channeled through dilution openings (not shown) in the outer liner 54 and the inner liner 52 into a dilution zone 75 of the combustion chamber 62 to provide quenching of the combustion gases 86 in the dilution zone 75. Further, or in the alternative, at least a portion of the compressed air 82(b) can be channeled out of the diffuser cavity 84 for other purposes, such as providing cooling air for at least one of the HP turbine 28 or the LP turbine 30.

[0029] Referring again to Figure 1 and Figure 2 , the combustion gases 86 produced in the combustion chamber 62 flow through the turbine nozzle 79 and into the HP turbine 28, thus causing the HP rotor shaft 34 to rotate, thereby supporting operation of the HP compressor 24. As Figure 1As shown, combustion gases 86 are then directed through the LP turbine 30, thus causing the LP rotor shaft 36 to rotate, thereby supporting operation of the LP compressor 22 and / or rotation of the fan shaft 38. The combustion gases 86 are then exhausted through the ejection exhaust nozzle section 32 of the core engine 16 to provide a propulsive force at the downstream end 99.

[0030] Figure 3 is a schematic partial cross-sectional view of a portion of the outer liner 54 taken at a detailed view 100 in Figure 2 Figure 3 The arrangement of the inner liner 52 is also applicable, and thus references to various inner liner elements can be included within the brackets in the figures. However, for brevity, the following description will be made with respect to elements of the outer liner 54. As shown in Figure 3 The outer liner 54 is a multi-layered liner that includes a cold side liner segment 102 and a hot side liner segment 104 arranged radially inward of the cold side liner segment 102. The cold side liner segment 102 is arranged adjacent to the outer flow passage 88, and the hot side liner segment 104 is arranged adjacent to the combustion chamber 62. A dam cavity 106 is defined between a first side 108 of the cold side liner segment 102 and a first side 110 of the hot side liner segment 104. The cold side liner segment 102 includes a plurality of cold side cooling airflow openings 114 therethrough to allow some of the compressed air 82(b) in the outer flow passage 88 to flow into the dam cavity 106, and the hot side liner segment 104 includes a plurality of hot side cooling airflow openings 116 extending therethrough from the first side 110 of the hot side liner segment 104 to a hot surface side 111 of the hot side liner segment 104 to allow the compressed air 82(b) to flow from the dam cavity 106 into the combustion chamber 62.

[0031] The outer liner 54 also includes at least one cooling airflow dispersion member 118 arranged within the dam cavity 106. While Figure 3 While one cooling airflow dispersion member 118 is depicted, the outer liner 54 and the inner liner 52 can include a plurality of cooling airflow dispersion members 118. For example, a plurality of cooling airflow dispersion members 118 can be circumferentially spaced about the outer liner 54, with a respective one of the cooling airflow dispersion members 118 arranged at a respective hot spot 68 in the combustor liner 50.

[0032] Figure 4 is a schematic partial cross-sectional view of a cooling airflow dispersion member 118 taken at a plane 4-4 of Figure 3 Referring collectively to Figure 3 and Figure 4 It can be seen that the cooling airflow dispersion member 118 includes a main cavity portion 120, a first peripheral cavity portion 122 surrounding the main cavity portion 120, and a second peripheral cavity portion 124 surrounding the first peripheral cavity portion 122. While Figure 3 and Figure 4 ​Two peripheral cavity portions 122 / 124 are depicted about the main cavity portion 120, but the present disclosure is not limited to two peripheral cavity portions, and additional peripheral cavity portions can be included in the cooling airflow dispersion member 118. In Figure 3 the main cavity portion 120 is shown extending from the first side 108 of the cold-side liner section 102 to the first side 110 of the hot-side liner section 104. The main cavity portion 120 is defined by a main cavity wall 126, as Figure 3 shown, the main cavity wall 126 extends from the first side 108 of the cold-side liner section 102 to the first side 110 of the hot-side liner section 104. However, in some aspects, a leakage gap or a plurality of leakage openings (not shown) can be provided between the hot-side end 129 of the main cavity wall 126 and the first side 110 of the hot-side liner section 104, and / or can be provided between the cold-side end 133 of the main cavity wall 126 and the first side 108 of the cold-side liner section 102. Thus, the main cavity wall 126 can be connected to the cold-side liner section 102 and / or the hot-side liner section 104. In Figure 4 the main cavity wall 126 is shown as a generally cylindrical wall that defines a main cavity wall perimeter 127. Of course, the main cavity wall 126 is not limited to a cylindrical wall, but can instead use other shapes to define the main cavity portion 120. The main cavity portion 120 is also defined by a main cavity inlet side 128, which can be a portion of the cold-side liner section 102, and a main cavity outlet side 130, which can be a portion of the hot-side liner section 104. The main cavity wall 126 can be bonded to the cold-side liner section 102 and the hot-side liner section 104 via, for example, welding or brazing. The main cavity inlet side 128 includes at least one of the plurality of cold-side cooling airflow openings 114 that provide a flow of compressed air 82(b) from the outer flow passage 88 to the main cavity portion 120. For example, the main cavity inlet side 128 can include a main cavity inlet opening 132 as one of the plurality of cold-side cooling airflow openings 114, where the main cavity inlet opening 132 is sized larger than the cold-side cooling airflow openings 114. Further, the main cavity wall 126 can include a plurality of main cavity leakage openings 131 that provide a leakage cooling air flow from the main cavity portion 120 to the baffle cavity 106. The main cavity outlet side 130 can also include at least one of the hot-side cooling airflow openings 116, while providing impingement cooling to the hot-side liner section 104. As Figure 4 shown, the main cavity outlet side 130 can include four hot-side cooling airflow openings 116. Of course, the main cavity outlet side 130 is not limited to four hot-side cooling airflow openings 116, but can instead include more or fewer hot-side cooling airflow openings 116. Further, the main cavity outlet side 130 can not include any hot-side cooling airflow openings 116, but instead provide impingement cooling only to the main cavity outlet side 130.

[0033] The main cavity portion 120 also includes at least one peripheral cavity outlet flow passage 134 for providing fluid communication between the main cavity portion 120 and the first peripheral cavity portion 122. In Figure 3 and Figure 4 aspects, four peripheral cavity outlet flow passages 134 are shown, and each peripheral cavity outlet flow passage 134 is shown extending through the main cavity wall 126. Each peripheral cavity outlet flow passage 134 can be arranged at an angle 137 so as to direct a flow of cooling air through the peripheral cavity outlet flow passage 134 onto a first peripheral cavity outlet side 164 of the first peripheral cavity portion 122.

[0034] The first peripheral cavity portion 122 includes a first peripheral cavity wall 136, as Figure 4 shown, the first peripheral cavity wall 136 defines a first peripheral cavity wall perimeter 138 defined by an upstream side 198, a first side 214, a downstream side 200, and a second side 216, the first peripheral cavity wall perimeter 138 surrounds the main cavity wall perimeter 127 and has a first gap 140 therebetween. Similarly, the second peripheral cavity portion 124 includes a second peripheral cavity wall 142, as Figure 4 shown, the second peripheral cavity wall 142 defines a second peripheral cavity wall perimeter 144 defined by an upstream side 206, a first side 218, a downstream side 208, and a second side 220, the second peripheral cavity wall 142 has a second gap 146 between the first peripheral cavity wall 136 and the second peripheral cavity wall 142. In Figure 4 aspects, the main cavity wall 126 is shown as a circular shape, while the first peripheral cavity wall 136 and the second peripheral cavity wall 142 are each shown as defining a rectangular shape. However, other shapes can alternatively be implemented, as Figures 5 to 8 shown.

[0035] Figures 5 to 8 are various schematic views depicting examples of respective shapes that can be implemented for each of the main cavity wall 126, the first peripheral cavity wall 136, and the second peripheral cavity wall 142. In Figure 5 and 6 , each of the main cavity wall 126, the first peripheral cavity wall 136, and the second peripheral cavity wall 142 are shown as a circular shape. In Figure 5 , each of the main cavity wall 126, the first peripheral cavity wall 136, and the second peripheral cavity wall 142 are also shown as being arranged concentrically with respect to one another about a center 148 of the main cavity wall 126. Each of the main cavity wall 126, the first peripheral cavity wall 136, and the second peripheral cavity wall 142 are symmetric about a centerline 150 through the center 148, the centerline 150 being perpendicular to the flow direction 85. However, in Figure 6 , each of the first peripheral cavity wall 136 and the second peripheral cavity wall 142 are shown as being offset from the centerline 150, such that each of the first peripheral cavity wall 136 and the second peripheral cavity wall 142 are asymmetric with respect to the centerline 150. As another example, asFigure 7 As shown, the primary cavity wall 126 can be circular, while the first peripheral cavity wall 136 and the second peripheral cavity wall 142 are both elliptical walls. In Figure 8 In the example aspect, the primary cavity wall 126 is again shown as a circular shape, while the first peripheral cavity wall 136 is a pentagonal shape and the second peripheral cavity wall 142 is a hexagonal shape. Thus, the shapes of the primary cavity wall 126, the first peripheral cavity wall 136, and the second peripheral cavity wall 142 are not limited to any particular shape.

[0036] In the example aspect, the first peripheral cavity wall 136 is shown as extending from the first side 108 of the cold-side liner section 102 to the first side 110 of the hot-side liner section 104. More specifically, the first peripheral cavity wall 136 includes a first end 152 connected to the first side 110 of the hot-side liner section 104, and a second end 154 extending from the first end 152 into the baffle cavity 106 at a first distance 156. The first distance 156 can define a height of the first peripheral cavity portion 122. Figure 3 The first peripheral cavity portion 122 further includes a first peripheral cavity encompassing wall 158 extending from the primary cavity wall 126 to the second end 154 of the first peripheral cavity wall 136. The first peripheral cavity encompassing wall 158 further extends around the primary cavity wall perimeter 127 to the first peripheral cavity wall perimeter 138. That is, in

[0037] In the example aspect, the first peripheral cavity encompassing wall 158 can be a rectangular shaped sheet with an outer perimeter end 160 connected to the second end 154 of the first peripheral cavity wall 136. In Figure 3 In the example aspect, the primary cavity opening 162 can be a circular aperture included in the first peripheral cavity encompassing wall 158 and connected to the primary cavity wall 126. In 4 In the example aspect, the first peripheral cavity encompassing wall 158 is shown as being arranged generally parallel to both the cold-side liner section 102 and the hot-side liner section 104. Thus, the first peripheral cavity encompassing wall 158 encompasses the first peripheral cavity portion 122, thereby defining the first peripheral cavity portion 122 between the primary cavity wall 126, the first peripheral cavity encompassing wall 158, the first peripheral cavity wall 136, and the hot-side liner section 104. Figure 3 4 Figure 3

[0038] ​​​The first peripheral cavity wall 136 includes a plurality of first peripheral cavity wall outlet openings 157 that provide fluid communication between the first peripheral cavity portion 122 and the second peripheral cavity portion 124. As will be described in greater detail below, cooling air 82(c) from the first peripheral cavity portion 122 flows through the plurality of first peripheral cavity wall outlet openings 157 into the second peripheral cavity portion 124. Each peripheral cavity wall outlet opening 157 can be arranged at an angle 139 so as to direct cooling air 82(c) flowing through the peripheral cavity wall outlet opening 157 onto a second peripheral cavity outlet side 180 of the second peripheral cavity portion 124. The first peripheral cavity portion 122 also includes a first peripheral cavity outlet side 164 that includes at least one of the plurality of hot side cooling airflow openings 116 therethrough. The plurality of hot side cooling airflow openings 116 through the first peripheral cavity outlet side provide a flow 228 Figure 11 of cooling air 82(c) to flow from the first peripheral cavity portion 122 to the hot surface side 59 of the hot side liner segment 104. As shown, the plurality of hot side cooling airflow openings 116 in the first peripheral cavity portion 122 can be dispersedly arranged about the first peripheral cavity outlet side 164, where the dispersed arrangement can be based on a temperature gradient of the hot side liner segment 104 about an area of the first peripheral cavity outlet side 164 so as to provide cooling airflow to an area having a highest temperature. Figure 4

[0039] In Figure 3 , it can be seen that the second peripheral cavity wall 142 extends partially from between the first side 108 of the cold side liner segment 102 and the first side 110 of the hot side liner segment 104 to the first side 110 of the hot side liner segment 104. More specifically, the second peripheral cavity wall 142 includes a third end 166 connected with the first side 110 of the hot side liner segment 104 and a fourth end 168 extending from the third end 166 into the baffle cavity 106 at a second distance 170, where the second distance 170 is less than the first distance 156. Thus, the second distance 170 can define a height of the second peripheral cavity portion 124.

[0040] The second peripheral cavity portion 124 also includes a second peripheral cavity encompassing wall 172 extending from the first peripheral cavity wall 136 to the fourth end 168 of the second peripheral cavity wall 142. The second peripheral cavity encompassing wall 172 further extends about the first peripheral cavity wall periphery 138 to the second peripheral cavity wall periphery 144. That is, in the exemplary aspects of Figure 3 and Figure 4 , the second peripheral cavity encompassing wall 172 can be a rectangular shaped sheet, where an outer periphery end 174 is connected to the fourth end 168 of the second peripheral cavity wall 142. In Figure 3 and Figure 4 , the first peripheral cavity opening 176 can be a rectangular aperture included in the second peripheral cavity encompassing wall 172 and connected to the first peripheral cavity wall 136. In​Figure 3 In aspects of the second peripheral cavity, the second peripheral cavity-enclosing wall 172 is shown as being arranged generally parallel to both the cold-side liner segment 102 and the hot-side liner segment 104. Thus, the second peripheral cavity-enclosing wall 172 encloses the second peripheral cavity portion 124 so as to define the second peripheral cavity portion 124 between the first peripheral cavity wall 136, the second peripheral cavity-enclosing wall 172, the second peripheral cavity wall 142, and the hot-side liner segment 104.

[0041] The second peripheral cavity wall 142 can also include a plurality of second peripheral cavity wall outlet openings 178 that provide fluid communication between the second peripheral cavity portion 124 and the baffle cavity 106. However, the plurality of second peripheral cavity wall outlet openings 178 can be omitted. The second peripheral cavity portion 124 also includes a second peripheral cavity outlet side 180 that includes at least one of the plurality of hot-side cooling airflow openings 116 therethrough. The plurality of hot-side cooling airflow openings 116 through the second peripheral cavity outlet side 180 provide a flow of cooling air 82(c) to flow from the second peripheral cavity portion 124 to the hot surface side 59 of the hot-side liner segment 104. As shown, the plurality of hot-side cooling airflow openings 116 in the second peripheral cavity portion 124 can be arranged dispersedly about the second peripheral cavity outlet side 180, where the dispersed arrangement can be based on a temperature gradient of the hot-side liner segment 104 about an area of the second peripheral cavity outlet side 180 so as to provide cooling airflow to a highest temperature area. Figure 4

[0042] Figure 9 is a detailed view of a portion of the outer liner 54 taken at the detailed view 100 in Figure 2 is a schematic partial cross-sectional view of a portion of the outer liner 54 taken at the detailed view 100 in Figure 9 Aspects of the detailed view 100 are similar to aspects of the detailed view 100 in Figure 3 Thus, the same reference numerals shown in the detailed view 100 will not be described further. Figure 9 Aspects of the detailed view 100 are similar to aspects of the detailed view 100 in Figure 3 Thus, the same reference numerals shown in the detailed view 100 will not be described further. Figure 9 ​In this aspect, the main cavity portion 120 includes a main cavity baffle 182 disposed within the main cavity portion between the first side 108 of the cold-side bushing section 102 and the first side 110 of the hot-side bushing section 104. Thus, with respect to the main cavity baffle 182, a first main cavity portion 186 is defined between the first side 108 of the cold-side bushing section 102 and the main cavity baffle 182, and a second main cavity portion 188 is defined between the main cavity baffle 182 and the first side 110 of the hot-side bushing section 104. A plurality of peripheral cavity outlet flow channels 134 are included within the second main cavity portion 188. The main cavity baffle 182 includes a main cavity baffle opening 184 through which at least one main cavity baffle opening 184 allows cooling air 82(c) to flow from the first main cavity portion 186 into the second main cavity portion 188. As will be described in more detail below, the main cavity baffle 182 may be arranged within the main cavity portion 120 at a distance 190 from the first side 110 of the hot-side bushing section 104. The distance 190 to the main cavity baffle 182 may be adjusted based on the desired amount of impact cooling to be provided to the main cavity outlet side 130 in the second main cavity portion 188.

[0043] exist Figure 9 In this regard, the main cavity portion 120, the first peripheral cavity portion 122, and the second peripheral cavity portion 124 are all considered to include a plurality of turbulence generators 192 arranged on the first side 110 of the hot-side bushing section 104. The turbulence generators 192 are typically impellers that extend from the first side 110 of the hot-side bushing section 104 into the respective cavities (i.e., into the main cavity portion 120, the first peripheral cavity portion 122, and the second peripheral cavity portion 124).

[0044] Figure 10 Based on aspects of this disclosure Figure 9 A schematic partial cross-sectional view of the cooling airflow dispersion component 118 taken at plane 10-10. Figure 10 The aspects include the arrangement of the main cavity wall 126, the first peripheral cavity wall 136, and the second peripheral cavity wall 142, which are similar to Figure 6 The arrangement is shown in the diagram. That is, each of the main cavity wall 126, the first peripheral cavity wall 136, and the second peripheral cavity wall 142 is a generally circular wall defining a circular cavity. In each cavity section, a plurality of turbulence generators 192 are spaced apart in a generally circumferential direction relative to the circular cavity to generate turbulence and introduce swirls into the airflow entering the respective cavity.

[0045] Figure 11 It is based on another aspect of this disclosure. Figure 2 A schematic partial cross-sectional view of a portion of the outer liner 54, taken at point 100 in the detailed view. Figure 11 Similar to Figure 9 Therefore, the same reference numerals will no longer be used in these aspects. However, in Figure 11In the diagram, the first peripheral cavity surrounding wall 158 is shown arranged at an angle 194, and the second peripheral cavity surrounding wall 172 is shown arranged at an angle 196. Therefore, the upstream side 198 of the first peripheral cavity wall 136 can have a height 202, and the downstream side 200 of the first peripheral cavity wall 136 can have a height 204, which is less than the height 202. Similarly, the upstream side 206 of the second peripheral cavity wall 142 can have a height 210, and the downstream side 208 of the second peripheral cavity wall 142 can have a height 212, which is less than the height 210. (Return to Reference) Figure 4 For the first peripheral cavity wall 136, the first side 214 of the first peripheral cavity wall 136 and the second side 216 of the peripheral cavity wall 136 ( Figure 4 The height 202 transitions from the upstream side 198 of the first peripheral cavity wall 136 to the downstream side 200 at a height 204. Similarly, for the second peripheral cavity wall 142, the first side 218 of the second peripheral cavity wall 142 and the second side 220 of the second peripheral cavity wall 142 ( Figure 4 The height 210 at the upstream side 206 transitions to the height 212 at the downstream side 208. Therefore, the first peripheral cavity portion 122 can provide a more compressed airflow on the downstream side 200 than on the upstream side 198, thereby providing a greater flow velocity on the downstream side 200, and the second peripheral cavity portion 124 can similarly provide a more compressed airflow on the downstream side 208 than on the upstream side 206, thereby providing a greater flow velocity on the downstream side 208 than on the upstream side 206.

[0046] Refer again Figure 11 The bushing cooling process, in which localized cooling is provided to the hot-side bushing section 104 via the cooling airflow dispersion member 118, will now be described. As described above, compressed air 82(b) flows in the outer flow channel 88 in the flow direction 85. The compressed air 82(b) is used to implement the cooling process, and the compressed air 82(b) used by the cooling airflow dispersion member 118 will be referred to hereinafter as cooling air 82(c). The main cavity inlet opening 132 on the main cavity inlet side 128 is arranged to provide a first flow 222 of cooling air 82(c) into the main cavity section 120. In the main cavity section 120, including the main cavity baffle 182... Figure 11In aspects of 82(c) into the first main cavity portion 186 and then through the main cavity baffle openings 184 into the second main cavity portion 188. The first flow 222 of cooling air 82(c) impinges the main cavity outlet side 130 of the hot side liner segment 104 within the main cavity portion 120. As described above, hot spots 68 can be present on the hot side liner segment 104 and the impingement of the first flow 222 of cooling air 82(c) provides backside cooling to the hot side liner segment 104 at the hot spots 68. Due to the presence of the main cavity baffle 182, the first flow 222 of cooling air 82(c) impinging the main cavity outlet side 130 can oscillate back and forth between the main cavity outlet side 130 and the main cavity baffle 182 within the second main cavity portion 188, thereby providing longer exposure time for the cooling air 82(c) to impinge the main cavity outlet side 130. In addition, the plurality of hot side cooling airflow openings 116 of the main cavity outlet side 130 are configured to provide a second flow 224 of cooling air 82(c) from the main cavity portion 120 to the hot surface side 59 of the hot side liner segment 104. The second flow 224 of cooling air 82(c) can provide film cooling of the hot surface side 59 of the hot side liner segment 104.

[0047] The peripheral cavity outlet flow channels 134 through the main cavity wall 126 are configured to provide a third flow 226 of cooling air 82(c) from the main cavity portion 120 into the first peripheral cavity portion 122. The third flow 226 of cooling air 82(c) into the first peripheral cavity portion 122 impinges the first peripheral cavity outlet side 164 in order to provide backside cooling to the hot side liner segment 104 in the region of the hot side liner segment corresponding to the first peripheral cavity outlet side 164. The peripheral cavity outlet flow channels 134 can be arranged at an angle 135 Figure 10 ) which can have a range from 60 degrees to negative 60 degrees. When the peripheral cavity outlet flow channels 134 are arranged at the angle 135, they can induce a swirl flow to the third flow 226 into the first peripheral cavity 122. In addition, the plurality of hot side cooling airflow openings 116 of the first peripheral cavity outlet side 164 are configured to provide a fourth flow 228 of cooling air 82(c) from the first peripheral cavity portion 122 to the hot surface side 59 of the hot side liner segment 104 in order to provide film cooling of the hot surface side 59 of the hot side liner segment 104. The plurality of first peripheral cavity wall outlet openings 157 are configured to provide a fifth flow 230 of cooling air 82(c) from the first peripheral cavity portion 122 into the second peripheral cavity portion 124. The fifth flow 230 of cooling air 82(c) impinges the second peripheral cavity outlet side 180, thereby providing backside cooling to the hot side liner segment 104 in the region corresponding to the second peripheral cavity outlet side 180. In addition, the first peripheral cavity wall outlet openings 157 can be arranged at an angle 159 Figure 10) arranged at an angle 159. The angle 159 can have a range from 60 degrees to negative 60 degrees. When the first peripheral cavity wall outlet openings 157 are arranged at the angle 159, they can induce a rotational flow of the fifth flow 230 into the second peripheral cavity 124. The plurality of hot side cooling airflow openings 116 of the second peripheral cavity outlet side 180 are configured to provide a sixth flow 232 of cooling air 82(c) from the second peripheral cavity portion 124 to the hot surface side 59 of the hot side liner segment 104 so as to provide film cooling to the hot surface side 59 of the hot side liner segment 104 corresponding to the second peripheral cavity outlet side 180. The plurality of second peripheral cavity wall outlet openings 178 can provide a seventh flow 234 of cooling air 82(c) to flow from the second peripheral cavity portion 124 into the baffle cavity 106. However, the second peripheral cavity wall outlet openings 178 can be omitted, and when the second peripheral cavity wall outlet openings 178 are omitted, cooling air 82(c) within the second peripheral cavity portion 124 is provided via the sixth flow 232 of cooling air 82(c).

[0048] The various elements of the cooling airflow dispersion member 118 are configured to provide a relatively uniform velocity of the airflow into the combustion chamber 62 through each of the plurality of hot side cooling airflow openings 116. More specifically, parameters of each of the various elements are considered so as to achieve a relatively uniform velocity between the second flow 224, the fourth flow 228, and the sixth flow 232. Some of the parameters considered are: the size of the main cavity wall perimeter 127, the size of the first peripheral cavity wall perimeter 138, and the first distance 156 (i.e., the height of the first peripheral cavity wall 136), the size of the second peripheral cavity wall perimeter 144, and the second distance 170 (i.e., the height of the second peripheral cavity wall 142), the number and size of the peripheral cavity outlet flow passages 134, the number and size of the first peripheral cavity wall outlet openings 157, the number and size of the hot side cooling airflow openings 116 through the main cavity outlet side 130, the number and size of the hot side cooling airflow openings 116 through the first peripheral cavity outlet side 164, and the number and size of the hot side cooling airflow openings 116 through the second peripheral cavity outlet side 180.

[0049] Figure 12 is a schematic partial cross-sectional view of a portion of the outer liner 54 taken at the detailed view 100 in Figure 2 is a schematic partial cross-sectional view of a portion of the outer liner 54 taken at the detailed view 100 in Figure 12 In aspects of the 100, the cooling airflow dispersion member 118 is formed as a continuous-shaped structural element 119 shaped to define the main cavity portion 120, the first peripheral cavity portion 122, and the second peripheral cavity portion 124. That is, the continuous-shaped structural element 119 can be formed from, for example, a single sheet of metal or foil that is stamped, bent, formed, hammered, or otherwise manipulated so as to form the various cavities of the cooling airflow dispersion member 118 as the continuous-shaped structural element 119. Reference is made toFigure 13 , Figure 13 is a partial cross-sectional view taken at the plane 13-13 of Figure 12 , the cooling airflow dispersion member 118 is shown as generally formed to define each of the main cavity portion 120, the first peripheral cavity portion 122, and the second peripheral cavity portion 124 as concentric circular cavities with one another. Of course, other shapes of the continuous shape structural element 119 can be alternatively implemented, including for example any of the shapes shown in Figures 5 to 8 . In Figure 12 and Figure 13 , a first transition portion 236 is formed between the main cavity portion 120 and the first peripheral cavity portion 122, and a second transition portion 238 is formed between the first peripheral cavity portion 122 and the second peripheral cavity portion 124. In aspects of Figure 12 , the at least one peripheral cavity outlet flow passage 134 can include a first transition portion gap 240 disposed between the first transition portion 236 and the first side 110 of the hot side liner segment 104. The first transition portion gap 240 provides a third flow 226 of cooling air 82(c) from the main cavity portion 120 to the first peripheral cavity portion 122 in a similar manner as described above with respect to Figure 11 . Similarly, a second transition portion gap 242 can be disposed between the second transition portion 238 and the first side 110 of the hot side liner segment 104 to provide a fifth flow 230 of cooling air 82(c) from the first peripheral cavity portion 122 to the second peripheral cavity portion 124. A hot side flange 244 can be connected to the hot side liner segment 104 via, for example, brazing. A first end 250 of a connecting wall 246 is attached to the hot side flange 244, and a cold side flange 248 is attached to a second end of the connecting wall 246. The cold side flange 252 can be connected to the cold side liner segment 102 via, for example, brazing.

[0050] In aspects of Figure 12 , the first peripheral cavity portion 122 can further include a plurality of first peripheral cavity inlet openings 254 for providing additional cooling air 82(c) from the baffle cavity 106 directly into the first peripheral cavity portion 122. The second peripheral cavity portion 124 can further include a plurality of second peripheral cavity inlet openings 256 for providing additional cooling air 82(c) from the baffle cavity 106 directly into the second peripheral cavity portion 124. Further, an air cavity 258 of the baffle cavity 106 between the cold side liner segment 102 and the shaped continuous shape structural element 119 can be filled with a metal foam or lattice filament element 260 between the first side 108 of the cold side liner segment 102 and a cold side 262 of the continuous shape structural element 119.

[0051] While the foregoing description generally relates to a gas turbine engine, it can be readily appreciated that the gas turbine engine can be implemented in a variety of environments. For example, the engine can be implemented in an aircraft, but can also be implemented in non-aircraft applications, such as power generation plants, marine applications, or oil and gas production applications. Accordingly, the present disclosure is not limited to use in an aircraft.

[0052] Further aspects of the present disclosure are provided by the subject matter of the following clauses.

[0053] A combustor liner for a gas turbine, the combustor liner comprising: a cold side liner segment comprising a plurality of cold side cooling airflow openings therethrough; a hot side liner segment disposed inboard of the cold side liner segment and comprising a plurality of hot side cooling airflow openings therethrough; a dam cavity defined between a first side of the cold side liner segment and a first side of the hot side liner segment; and at least one cooling airflow dispersion member disposed within the dam cavity, the at least one cooling airflow dispersion member comprising a main cavity portion and at least one peripheral cavity portion surrounding the main cavity portion, the main cavity portion comprising (i) a main cavity inlet side having at least one of the plurality of cold side cooling airflow openings, (ii) a main cavity outlet side for providing impingement cooling to a portion of the hot side liner segment, and (iii) at least one peripheral cavity outlet flow passage providing fluid communication between the main cavity portion and the at least one peripheral cavity portion, and the at least one peripheral cavity portion comprising a peripheral cavity outlet side having at least one of the plurality of hot side cooling airflow openings.

[0054] The combustor liner according to the preceding clause, wherein the at least one cooling airflow dispersion member comprises a plurality of cooling airflow dispersion members, each respective cooling airflow dispersion member being disposed at a high temperature region of the combustor liner.

[0055] The combustor liner according to any preceding clause, wherein at least one of the main cavity portion and the at least one peripheral cavity portion comprises a plurality of turbulators disposed on the first side of the hot side liner segment.

[0056] The combustor liner according to any preceding clause, wherein the main cavity portion comprises a main cavity dam disposed within the main cavity portion between the first side of the cold side liner segment and the first side of the hot side liner segment, the main cavity dam comprising a plurality of dam openings therethrough.

[0057] The combustor liner according to any preceding clause, wherein a first primary cavity portion is defined between the first side of the cold side liner segment and the primary cavity dam, a second primary cavity portion is defined between the primary cavity dam and the first side of the hot side liner segment, and the at least one peripheral cavity outlet flow passage is disposed in the second primary cavity portion.

[0058] The combustor liner according to any preceding clause, wherein the primary cavity portion extends between the first side of the cold side liner segment and the first side of the hot side liner segment, and the at least one peripheral cavity portion extends partially from between the first side of the cold side liner segment and the first side of the hot side liner segment to the first side of the hot side liner segment.

[0059] The combustor liner according to any preceding clause, wherein the at least one cooling gas flow dispersion member comprises a continuous shape structural element shaped to define the primary cavity portion and the at least one peripheral cavity portion, and comprising a transition portion between the primary cavity portion and the at least one peripheral cavity portion.

[0060] The combustor liner according to any preceding clause, wherein the at least one peripheral cavity outlet flow passage is provided between the transition portion and the hot side liner segment.

[0061] The combustor liner according to any preceding clause, wherein the continuous shape structural element is a formed sheet metal, the formed sheet metal being connected to the cold side liner segment along a cold side flange of the continuous shape structural element and to the hot side liner segment along a hot side flange of the continuous shape structural element.

[0062] The combustor liner according to any preceding clause, wherein a filament element is provided between the first side of the cold side liner segment and a cold side of the continuous shape structural element.

[0063] The combustor liner according to any preceding clause, wherein the primary cavity portion is defined by a primary cavity wall extending from the first side of the cold side liner segment to the first side of the hot side liner segment, and each of the at least one peripheral cavity portion is defined by a respective peripheral cavity wall having a respective peripheral wall perimeter surrounding a primary cavity wall perimeter of the primary cavity wall.

[0064] The combustor liner according to any preceding clause, wherein the at least one peripheral cavity portion comprises a first peripheral cavity portion having a first peripheral cavity wall defining a first peripheral cavity wall perimeter surrounding the main cavity wall perimeter with a first gap therebetween, and a second peripheral cavity portion having a second peripheral cavity wall defining a second peripheral cavity wall perimeter surrounding the first peripheral cavity wall perimeter with a second gap therebetween.

[0065] The combustor liner according to any preceding clause, wherein the first peripheral cavity wall comprises a plurality of first peripheral cavity wall outlet openings therethrough providing fluid communication between the first peripheral cavity portion and the second peripheral cavity portion.

[0066] The combustor liner according to any preceding clause, wherein the first peripheral cavity portion comprises a first peripheral cavity outlet side having at least one of the plurality of hot side cooling gas flow openings, and the second peripheral cavity portion comprises a second peripheral cavity outlet side having at least one of the plurality of hot side cooling gas flow openings.

[0067] The combustor liner according to any preceding clause, wherein the first peripheral cavity wall defines a first peripheral cavity wall perimeter and comprises a first end connected with the first side of the hot side liner segment and a second end extending from the first end into the damper cavity at a first distance, and the second peripheral cavity wall defines a second peripheral cavity wall perimeter and comprises a third end connected with the first side of the hot side liner segment and a fourth end extending from the third end into the damper cavity at a second distance less than the first distance.

[0068] The combustor liner according to any preceding clause, wherein the main cavity wall perimeter, the first peripheral cavity wall perimeter, and the second peripheral cavity wall perimeter at the first side of the hot side liner segment are symmetric with one another.

[0069] The combustor liner according to any preceding clause, wherein the main cavity wall perimeter, the first peripheral cavity wall perimeter, and the second peripheral cavity wall perimeter at the first side of the hot side liner segment are asymmetric with one another.

[0070] The combustor liner according to any preceding clause, wherein the first peripheral cavity portion includes a first peripheral cavity encompassing wall extending from the main cavity wall to the second end of the first peripheral cavity wall and extending around the main cavity wall perimeter and the first peripheral cavity wall perimeter, the second peripheral cavity portion includes a second peripheral cavity encompassing wall extending from the first peripheral cavity wall to the fourth end of the second peripheral cavity wall and extending around the first peripheral cavity wall perimeter and the second peripheral cavity wall perimeter.

[0071] The combustor liner according to any preceding clause, wherein the cold side liner segment is adjacent to an outer flow passage of a combustor and the hot side liner segment is adjacent to a combustion chamber of the combustor.

[0072] The combustor liner according to any preceding clause, wherein the at least one cold side cooling air flow opening of the main cavity inlet side is arranged to provide a first cooling air flow into the main cavity portion to impinge the main cavity outlet side of the hot side liner segment, the main cavity portion includes at least one of the plurality of hot side cooling air flow openings through the main cavity outlet side, the at least one of the plurality of hot side cooling air flow openings is configured to provide a second cooling air flow from the main cavity portion to a hot surface side of the hot side liner segment, the at least one peripheral cavity outlet flow passage is configured to provide a third cooling air flow from the main cavity portion into the first peripheral cavity portion, at least one of the plurality of hot side cooling air flow openings of the first peripheral cavity outlet side is configured to provide a fourth cooling air flow from the first peripheral cavity portion to the hot surface side of the hot side liner segment, the plurality of first peripheral cavity wall outlet openings are configured to provide a fifth cooling air flow from the first peripheral cavity portion into the second peripheral cavity portion, and at least one of the hot side cooling air flow openings of the second peripheral cavity outlet side is configured to provide a sixth cooling air flow from the second peripheral cavity portion to the hot surface side of the hot side liner segment.

[0073] While the forgoing has been set forth in terms of certain illustrative embodiments, other variations and modifications will be apparent to those skilled in the art and can be made without departing from the spirit or scope of the disclosure. Further, features described in connection with one embodiment can be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A combustor liner for a gas turbine, characterized by, comprises: a cold-side liner segment comprising a plurality of cold-side cooling airflow openings therethrough; a hot-side liner segment disposed inward of the cold-side liner segment and comprising a plurality of hot-side cooling airflow openings therethrough; a baffle cavity defined between a first side of the cold-side liner segment and a first side of the hot-side liner segment; and at least one cooling airflow dispersion member disposed within the baffle cavity, the at least one cooling airflow dispersion member comprising a main cavity portion and a plurality of peripheral cavity portions surrounding the main cavity portion, the main cavity portion comprising (i) a main cavity wall defining a main cavity wall perimeter, (ii) a main cavity inlet side having at least one of the plurality of cold-side cooling airflow openings, (iii) a main cavity outlet side for providing impingement cooling to a portion of the hot-side liner segment, and (iv) at least one peripheral cavity outlet flow passage providing fluid communication between the main cavity portion and at least one of the plurality of peripheral cavity portions, and at least one of the plurality of peripheral cavity portions comprising a first peripheral cavity portion having a first peripheral cavity wall defining a first peripheral cavity wall perimeter surrounding the main cavity wall perimeter with a first gap therebetween, and a second peripheral cavity portion having a second peripheral cavity wall defining a second peripheral cavity wall perimeter surrounding the first peripheral cavity wall perimeter with a second gap therebetween, the first peripheral cavity portion and the second peripheral cavity portion comprising a peripheral cavity outlet side having at least one of the plurality of hot-side cooling airflow openings therethrough. wherein 2. The combustor liner according to claim 1, wherein, the at least one cooling airflow dispersion member comprises a plurality of cooling airflow dispersion members, each respective cooling airflow dispersion member being disposed at a high temperature region of the combustor liner. wherein 3. The combustor liner of claim 1, wherein the main cavity portion and at least one of the first peripheral cavity portion and the second peripheral cavity portion comprise a plurality of turbulators disposed on the first side of the hot-side liner segment. wherein 4. The combustor liner of claim 1, wherein the main cavity portion comprises a main cavity baffle disposed within the main cavity portion between the first side of the cold-side liner segment and the first side of the hot-side liner segment, the main cavity baffle comprising a plurality of baffle openings therethrough. wherein 5. The combustor liner according to claim 4, wherein, a first main cavity portion is defined between the first side of the cold-side liner segment and the main cavity baffle, a second main cavity portion is defined between the main cavity baffle and the first side of the hot-side liner segment, and the at least one peripheral cavity outlet flow passage is disposed in the second main cavity portion. wherein 6. The combustor liner of claim 1, wherein the main cavity portion extends between the first side of the cold-side liner segment and the first side of the hot-side liner segment, and the first peripheral cavity portion and the second peripheral cavity portion extend partially from between the first side of the cold-side liner segment and the first side of the hot-side liner segment to the first side of the hot-side liner segment. wherein 7. The combustor liner according to claim 6, wherein, ​ The at least one cooling airflow dispersion member includes a continuous shape structural element shaped to define the main cavity portion and the first and second peripheral cavity portions, and including a first transition portion between the main cavity portion and the first peripheral cavity portion and a second transition portion between the first and second peripheral cavity portions.

8. The combustor liner according to claim 7, wherein, wherein, The at least one peripheral cavity outlet flow passage is disposed between the first transition portion and the hot side liner segment.

9. The combustor liner according to claim 7, wherein, wherein, The continuous shape structural element is a formed sheet metal connected to the cold side liner segment along a cold side flange of the continuous shape structural element and connected to the hot side liner segment along a hot side flange of the continuous shape structural element.

10. The combustor liner according to claim 9, wherein, wherein, A filament element is disposed between the first side of the cold side liner segment and a cold side of the continuous shape structural element.

11. The combustor liner of claim 1, wherein wherein, The main cavity wall extends from the first side of the cold side liner segment to the first side of the hot side liner segment, and the at least one peripheral cavity outlet flow passage is disposed through the main cavity wall.

12. The combustor liner according to claim 1, wherein, wherein, The first peripheral cavity wall includes a plurality of first peripheral cavity wall outlet openings therethrough providing fluid communication between the first and second peripheral cavity portions.

13. The combustor liner according to claim 12, wherein, wherein, The first peripheral cavity portion includes a first peripheral cavity outlet side having at least one of the plurality of hot side cooling airflow openings, and the second peripheral cavity portion includes a second peripheral cavity outlet side having at least one of the plurality of hot side cooling airflow openings.

14. The combustor liner according to claim 13, wherein, wherein, The first peripheral cavity wall includes a first end connected to the first side of the hot side liner segment and a second end extending from the first end into the baffle cavity at a first distance, and the second peripheral cavity wall includes a third end connected to the first side of the hot side liner segment and a fourth end extending from the third end into the baffle cavity at a second distance less than the first distance.

15. The combustor liner according to claim 14, wherein, wherein, The main cavity wall periphery, the first peripheral cavity wall periphery, and the second peripheral cavity wall periphery at the first side of the hot side liner segment are symmetrical to each other.

16. The combustor liner according to claim 14, wherein wherein, The main cavity wall periphery, the first peripheral cavity wall periphery, and the second peripheral cavity wall periphery at the first side of the hot side liner segment are asymmetrical to each other.

17. The combustor liner as in claim 14, wherein wherein, The first peripheral cavity portion includes a first peripheral cavity encompassing wall extending from the main cavity wall to the second end of the first peripheral cavity wall and around the main cavity wall periphery and the first peripheral cavity wall periphery, and the second peripheral cavity portion includes a second peripheral cavity encompassing wall extending from the first peripheral cavity wall to the fourth end of the second peripheral cavity wall and around the first peripheral cavity wall periphery and the second peripheral cavity wall periphery.

18. The combustor liner according to claim 17, wherein, wherein, The cold side liner segment is adjacent to an outer flow passage of a combustor, and the hot side liner segment is adjacent to a combustion chamber of the combustor.

19. The combustor liner according to claim 18, wherein, wherein, At least one of the plurality of cold side cooling airflow openings on the main cavity inlet side is arranged to provide a first cooling air flow into the main cavity portion to impinge a main cavity outlet side of the hot side liner segment, the main cavity portion including through at least one of the plurality of hot side cooling airflow openings on the main cavity outlet side, the at least one of the plurality of hot side cooling airflow openings configured to provide a second cooling air flow from the main cavity portion to a hot surface side of the hot side liner segment, the at least one peripheral cavity outlet flow passage is configured to provide a third cooling air flow from the main cavity portion into the first peripheral cavity portion, at least one of the plurality of hot side cooling airflow openings on the first peripheral cavity outlet side is configured to provide a fourth cooling air flow from the first peripheral cavity portion to the hot surface side of the hot side liner segment, the plurality of first peripheral cavity wall outlet openings are configured to provide a fifth cooling air flow from the first peripheral cavity portion into the second peripheral cavity portion, and at least one of the hot side cooling airflow openings on the second peripheral cavity outlet side is configured to provide a sixth cooling air flow from the second peripheral cavity portion to the hot surface side of the hot side liner segment.

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