用于燃气涡轮的燃烧器的点火器外壳

Abstract

一种用于燃气涡轮的燃烧器，包括燃烧器衬里、围绕燃烧器衬里的外壳体、延伸穿过穿过衬里的点火器开口的点火器外壳、以及设置在点火器外壳内的点火器。点火器外壳包括外壳壁，该外壳壁包括在外壳壁的下游侧并且布置在外流动通道内的至少一个气流入口通道，以及在外壳壁内在下游侧的至少一个冷却通道。至少一个冷却通道从至少一个气流入口通道沿点火器外壳的长度延伸并穿过点火器外壳的内端，至少一个冷却通道与至少一个气流入口通道流体连通。

Description

Technical Field

[0001] This disclosure relates to an igniter housing for a burner of a gas turbine. Background Technology

[0002] Some gas turbine engines typically include a combustor comprising a housing that surrounds a liner defining a combustion chamber. The combustor may also include multiple swirl cups that inject a fuel-air mixture into the combustion chamber. The combustor may also include one or more igniters (i.e., spark plugs) connected to the housing and extending through openings in the liner to provide a spark for igniting the fuel-air mixture within the combustion chamber. Attached Figure Description

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

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

[0005] Figure 2 This is a partial cross-sectional side view of an exemplary burner according to one aspect of this disclosure.

[0006] Figure 3 It is based on one aspect of this disclosure Figure 2 A partial cross-sectional view of the igniter assembly taken at point 100 in the detail view.

[0007] Figure 4 It is based on one aspect of this disclosure Figure 3 A cross-sectional view of the igniter assembly taken at point 4-4 on the plane.

[0008] Figure 5 It is based on one aspect of this disclosure Figure 4 The view Figure 5-5 A view of the igniter housing taken from the rear and looking forward.

[0009] Figure 6 This is based on another aspect of this disclosure. Figure 4 Cross-sectional view of an alternative arrangement to the one shown.

[0010] Figure 7 It is based on one aspect of this disclosure Figure 6 The view Figure 7-7 A view of the igniter housing taken from the rear and looking forward.

[0011] Figure 8It is similar to another aspect of this disclosure. Figure 3 A partial cross-sectional view of the alternative ignition assembly to the ignition assembly.

[0012] Figure 9 It is based on one aspect of this disclosure Figure 8 A cross-sectional view of the alternative igniter assembly taken at plane 9-9.

[0013] Figure 10 It is similar to another aspect of this disclosure. Figure 3 A partial cross-sectional view of the alternative ignition assembly to the ignition assembly.

[0014] Figure 11 It is based on one aspect of this disclosure Figure 10 A cross-sectional view of the alternative igniter assembly taken at plane 11-11.

[0015] Figure 12 This is a partial cross-sectional view of an alternative igniter assembly according to another aspect of this disclosure.

[0016] Figure 13 It is based on one aspect of this disclosure Figure 12 A cross-sectional view of the alternative igniter assembly taken at plane 13-13.

[0017] Figure 14 This is based on one aspect of the disclosure. Figure 13 A cross-sectional view of an alternative igniter grommets arrangement to the depicted igniter grommets arrangement.

[0018] Figure 15 It is based on one aspect of this disclosure Figure 14 Rear view of the cylindrical wall taken at 15-15 on the plane, with the igniter removed.

[0019] Figure 16 This is based on one aspect of the disclosure. Figure 14 Cross-sectional view of the alternative igniter arrangement. Detailed Implementation

[0020] The features, advantages, and embodiments of this disclosure will be set forth or apparent from consideration of the following detailed description, drawings, and claims. Furthermore, it should be understood that the following detailed description is exemplary and intended to provide further explanation, and does not limit the scope of the claimed disclosure.

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

[0022] As used herein, the terms “first” or “second” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the individual components.

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

[0024] Some gas turbine engines typically include a combustor comprising a housing that surrounds a liner defining a combustion chamber. The combustor may also include multiple swirl cups that inject a fuel-air mixture into the combustion chamber. The combustor may also include one or more igniters (i.e., spark plugs) that extend through openings in the liner to provide a spark for igniting the fuel-air mixture within the combustion chamber. As the fuel-air mixture is ignited and combusted, hot combustion gases are formed within the combustion chamber and flow through the chamber to a turbine nozzle at the downstream end of the combustion chamber. The hot combustion gases impinge on the tip of the igniter and also on the openings in the liner. Over time, the hot combustion gases cause deterioration of the igniter tip and also damage to the liner at the igniter openings, particularly on the downstream side of the igniter openings.

[0025] This disclosure provides a technique for reducing stress caused by hot combustion gases on the liner at the ignition tip and ignition opening. More specifically, this disclosure provides an ignition housing in which an ignition is inserted, wherein the housing itself includes cooling channels within its walls. The cooling channels within the walls of the ignition housing may be located on a downstream side of the ignition housing and provide an outlet flow of cooling air downstream of the ignition opening in the liner. The ignition housing may also include a closed cooling cavity on an upstream side of the ignition housing, wherein the closed cooling cavity is in fluid communication with the cooling channels. As a result, cooling air can circulate within the ignition housing on the upstream side, thereby providing impingement cooling to the upstream side of the ignition housing. Thus, various aspects of this disclosure provide a cooling airflow downstream of the ignition opening in the liner, thereby reducing stress on the liner caused by hot combustion gases and improving the reliability of the liner.

[0026] Now refer to the attached diagram, Figure 1 This is a schematic partial cross-sectional side view of an exemplary high-bypass turbofan jet engine 10 (referred to herein as "engine 10"), which can be incorporated into various embodiments of this disclosure. Although further described below with reference to turbofan engines, the invention 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. Figure 1As shown, engine 10 has an axial centerline axis 12 extending from an upstream end 98 of engine 10 through it to a downstream end 99 of engine 10, for reference. Typically, engine 10 may include a fan assembly 14 and a core engine 16 disposed downstream of the fan assembly 14.

[0027] The core engine 16 typically includes a housing 18 defining an annular inlet 20. The housing 18 surrounds or at least partially forms the core engine 15 in a series flow relationship, the core engine having: a compressor section (22 / 24) including a low-pressure (LP) compressor 22 and a high-pressure (HP) compressor 24; a combustor 26; a turbine section (28 / 30) including a high-pressure (HP) turbine 28 and a low-pressure (LP) turbine 30; and an injection exhaust nozzle section 32. A high-pressure (HP) rotor shaft 34 drivesly connects the HP turbine 28 to the HP compressor 24. A low-pressure (LP) rotor shaft 36 drivesly connects the LP turbine 30 to the LP compressor 22. The LP rotor shaft 36 may also be connected to a fan shaft 38 of the fan assembly 14. In certain embodiments, such as Figure 1 As shown, the LP rotor shaft 36 can be connected to the fan shaft 38 via a reduction gear 40, for example in an indirect drive or gear drive configuration.

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

[0029] Figure 2 Is it like this? Figure 1 A partial cross-sectional side view of an exemplary combustor 26 of the core engine 16 shown. Figure 2 As shown, burner 26 typically includes a burner liner 50 having an inner liner 52 and an outer liner 54, and a dome assembly 56, which together define a combustion chamber 62. Although Figure 2 An annular burner with an inner and outer liner is depicted, but this disclosure can be implemented in other types of burners, such as canister burners or canister annular burners. Figure 2 In this process, both the inner liner 52 and the outer liner 54 can extend circumferentially around the burner centerline axis 112, which can correspond to the engine axial centerline axis 12. Figure 1The inner liner 52 and outer liner 54 are connected to the shroud 60, and the pressure chamber 66 is defined between the shroud 60, the inner liner 52, the outer liner 54, and the dome assembly 56. The burner 26 also includes a mixer assembly 58, which is connected to the fuel nozzle assembly 70. Although... 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 may be included in the burner 26, wherein each corresponding mixer assembly 58 and fuel nozzle assembly 70 is circumferentially spaced through the dome assembly 56 about the burner centerline axis 112.

[0030] like Figure 2 As shown, the inner liner 52 surrounds the inner housing 65, and the outer liner 54 surrounds the outer housing 64. An outer flow passage 88 is defined between the outer liner 54 and the outer housing 64, and an inner flow passage 90 is defined between the inner liner 52 and the inner housing 65. Both the outer housing 64 and the inner housing 65 can extend circumferentially about the burner centerline axis 112. The inner liner 52 and the outer liner 54 can extend from the dome assembly 56 to the HP turbine 28 (…). Figure 1 The turbine nozzle 68 at the inlet of the combustor liner 50 thus at least partially defines the hot gas path between the combustor liner 50 and the HP turbine 28. The combustion chamber 62 may more specifically define a primary combustion zone 74 where the initial chemical reaction of the fuel-oxidant mixture 72 occurs to produce combustion gases 86, and / or where the combustion gases 86 further flow downstream within the combustion chamber 62 and into the HP turbine 28 and LP turbine 30. Figure 1 The recirculation of combustion gas 86 can occur before the turbine nozzle 68 at the inlet of the turbine.

[0031] During the operation of engine 10, such as Figure 1 and Figure 2 As shown, as schematically indicated by arrow 73, a certain volume of air enters the engine 10 from the upstream end 98 through the associated nacelle inlet 76 of the nacelle 44 and / or fan assembly 14. As the air 73 passes through the fan blades 42, a portion of the air 73 is directed or directed as bypass airflow 78 into the bypass airflow passage 48, while another portion of the air 73 is directed or directed as compressor inlet air 80 into the annular inlet 20 and the LP compressor 22. The compressor inlet air 80 is gradually compressed as it flows through the LP compressor 22 and the HP compressor 24 towards the combustor 26. Figure 2As shown, compressed air 82 flows into diffuser cavity 84 and pressurizes diffuser cavity 84. As schematically indicated by arrow 82(a), a first portion of the compressed air 82 flows from diffuser cavity 84 into pressure chamber 66, where it is mixed with fuel supplied by fuel nozzle assembly 70 via mixer assembly 58 to produce fuel-oxidant mixture 72 injected into combustion chamber 62 via mixer assembly 58. Fuel-oxidant mixture 72 is ignited and burned by igniter assembly 75 to produce combustion gases 86 in primary combustion zone 74 of combustion chamber 62.

[0032] Typically, the LP compressor 22 and HP compressor 24 supply more compressed air 82 to the diffuser chamber 84 than is required for combustion. Therefore, a second portion of the compressed air 82, schematically indicated by arrow 82(b), can be used for various purposes other than combustion. For example, as... Figure 2 As shown, compressed air 82(b) can be directed into the outer flow passage 88, and another portion of compressed air 82(b) can be directed into the inner flow passage 90. Alternatively, at least a portion of compressed air 82(b) can be discharged from 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.

[0033] Return to common reference Figure 1 and 2 The combustion gases 86 generated in the combustion chamber 62 flow through the turbine nozzle 68 and enter the HP turbine 28, causing the HP rotor shaft 34 to rotate, thereby supporting the operation of the HP compressor 24. Figure 1 As shown, the combustion gases 86 are then directed through the LP turbine 30, causing the LP rotor shaft 36 to rotate, thereby supporting the operation of the LP compressor 22 and / or the rotation of the fan shaft 38. The combustion gases 86 are then discharged through the injection exhaust nozzle section 32 of the core engine 16 to provide propulsion at the downstream end 99.

[0034] Figure 3 It is based on one aspect of this disclosure Figure 2 A partial cross-sectional view of an exemplary igniter assembly, taken at point 100 in the detailed view. Figure 3 In the diagram, the outer liner 54 is shown as a two-piece liner comprising a housing portion 55 and a heat insulation portion 57, with a baffle cavity 59 between the housing portion 55 and the heat insulation portion 57. A grommets 61 may be provided between the housing portion 55 and the heat insulation portion 57 at the ignition opening 124 passing through the outer liner 54. The outer liner 54 is not limited to a two-piece liner and may also be implemented as a single-piece liner. Figure 3As shown, the igniter assembly 75 includes an igniter housing 102 and an igniter 104 disposed within the igniter housing 102. The igniter housing 102 can be configured to be coupled to a housing 64 via, for example, an adapter 106. For example, the igniter housing 102 may include an externally threaded portion 108 that threadedly engages with the adapter 106 to couple the igniter housing 102 to the adapter 106. The adapter 106 can in turn be coupled to the housing 64 via, for example, a bolt 110. Thus, the igniter housing 102 is configured to be coupled to the housing 64 via the adapter 106. The igniter 104 can be coupled to the igniter housing 102 via, for example, an internally threaded portion 126 of the igniter housing 102. An insulating layer 128 can be disposed between the igniter 104 and the igniter housing 102. A gasket 114 can be disposed between a shoulder 116 of the igniter housing 102 and a shoulder 118 of the adapter 106. The igniter housing 102, when coupled to the housing 64, extends through the outer flow channel 88 and through the igniter opening 124 passing through the outer liner 54, wherein a predetermined gap 125 is provided between the igniter housing 102 and the igniter opening 124. A gasket 114 can be configured to adjust the inner end 120 of the igniter housing 102 relative to the hot surface side 122 of the outer liner 54 (wherein...). Figure 3 The hot surface side 122 of the inner end 120 is aligned with the hot surface side of the insulation portion 57 forming part of the outer liner 54, such that the inner end 120 is arranged close to the hot surface side 122 of the outer liner 54. Here, close to can mean flush with the hot surface side 122, or it can mean within a given range of being flush with the hot surface side 122. As an example, when assembled under standard atmospheric conditions (e.g., 68°F and 1 atmosphere), the inner end 120 can be filled with a gasket 114 to arrange it within ±10 mm of the hot surface side 122. Of course, other ranges are also possible, and this disclosure is not limited to the ranges described above.

[0035] Figure 4 It is based on one aspect of this disclosure Figure 3 A cross-sectional view of the igniter assembly taken at point 4-4 on the plane. (Common Reference) Figure 3 and 4 The igniter housing 102 includes a housing wall 132 defining a periphery 130. Figure 4 As can be seen, the outer casing wall 132 defines a circular perimeter 133, and the outer casing wall 132 includes a cylindrical outer casing wall 135 having an axial opening 134 extending through it along a central axis 136. The igniter 104 is disposed within the axial opening 134. Although... Figure 4The peripheral 130 is depicted as a circular peripheral 133, and the housing wall 132 is depicted as a cylindrical housing wall 135, but other peripheral and housing wall shapes may be implemented instead of a circular peripheral and cylindrical housing wall. A centerline axis 136 defines an axial direction 138 for the igniter housing 102, while a flow axis 140 extending orthogonally to the centerline axis 136 defines an upstream direction 142 and a downstream direction 144, and a transverse axis 146 extending through the centerline axis 136 and orthogonally to the flow axis 140 defines a first transverse direction 148 and a second transverse direction 150. The flow axis 140 is generally parallel to the flow of compressed air 82(b) within the outer flow channel 88. The housing wall 132 includes a first side 152 (e.g., an upstream side) upstream of the centerline axis 136 and a second side 154 (e.g., a downstream side) downstream of the centerline axis 146 opposite to the first side.

[0036] The housing wall 132 includes at least one airflow inlet passage 156 on the second (downstream) side 154 of the housing wall 132. For example... Figure 4 As shown, at least one airflow inlet passage 156 includes a plurality of airflow inlet passages 156 arranged within an outer flow passage 88, such that, as described below, a portion of the compressed air 82(b) flowing within the outer flow passage 88 can flow into at least one airflow inlet passage 156. (See brief reference...) Figure 5 , Figure 5 Is Figure 4 The view Figure 5-5 The view taken from rear to front shows that at least one airflow inlet passage 156 includes a circular inlet passage 158 extending through the housing wall 132. The diameter 160 of each of the airflow inlet passages 156 and the number of airflow inlet passages 156 to be included in the housing wall 132 can be based on the amount of cooling airflow required to be supplied through the igniter housing 102. Although Figure 5 The entrance channel 156 is depicted as a circular entrance channel 158, but other shapes can be implemented for the entrance channel 156 and the entrance channel 156 is not limited to a circular shape.

[0037] Return to reference Figure 3 and 4 The housing wall 132 also includes at least one cooling channel 162 within the housing wall 132 on the second (downstream) side 154. Figure 4As can be seen, at least one cooling passage 162 includes a single cooling passage 162, but as will be described below, it may alternatively include multiple cooling passages 162. At least one cooling passage 162 extends from at least one airflow inlet passage 156 along the length 164 of the igniter housing 102 and through the inner end 120 of the igniter housing 102, such that at least one cooling passage 162 is in fluid communication with at least one airflow inlet passage 156 and the combustion chamber 62. Figure 4 At least one cooling channel 162 is shown as a slotted cooling channel 166 extending in the circumferential direction 168 on the second (downstream) side 154 of the housing wall 132 relative to the centerline axis 136 of the housing wall 132. The slotted cooling channel 166 is considered to be slotted in such a way that it has... Figure 4 The cross-sectional view shows the opening of the groove width and groove length, where the groove width can be obtained relative to the flow axis 140, and the groove length can be obtained around the centerline axis 136 relative to the center point of the groove width, as the radial length (or arc length). Figure 4 A slotted cooling channel 166 is depicted having a length of 180 degrees extending on the second (downstream) side 154 of the housing wall 132 in a downstream direction 144 relative to the transverse axis 146 and the flow axis 140. However, the slotted cooling channel 166 may extend less than 180 degrees on the second (downstream) side 154 of the housing wall 132, for example, extending 120 degrees (e.g., extending 60 degrees from the downstream direction 144 of the flow axis 140 toward a first transverse direction 148 toward the transverse axis 146, and extending 60 degrees from the downstream direction 144 of the flow axis 140 toward a second transverse direction 150 toward the transverse axis 146). Alternatively, the slotted cooling channel 166 may extend more than 180 degrees (e.g., extending 120 degrees from the downstream direction 144 of the flow axis 140 toward a first transverse direction 148 toward the transverse axis 146, and extending 120 degrees from the downstream direction 144 of the flow axis 140 toward a second transverse direction 150 toward the transverse axis 146).

[0038] In operation, as mentioned above... Figure 1 and 2 As described, a portion of the compressed air 82 within the diffuser cavity 84, schematically shown by arrow 82(b), flows into the external flow channel 88. Figure 3 and 4 In the middle, a portion of the compressed air 82(b) within the outer flow passage 88 passes through at least one airflow inlet passage 156 and then enters at least one cooling passage 162. Cooling airflow 82(c) flows from at least one cooling passage 162 at the inner end 120 of the igniter housing 102 to provide cooling to the downstream side 170 of the igniter opening 124 at the hot surface side 122 of the outer liner 54.

[0039] Figure 6 This is based on another aspect of this disclosure. Figure 4 A cross-sectional view of an alternative arrangement to the one shown. Figure 6 In this respect, it can be seen that the igniter housing 102 includes multiple cooling channels 172 instead of a single cooling channel 162. Each of the multiple cooling channels 172 may be similar to the cooling channel 162 in that they may be slotted cooling channels extending along a length 164 of the second (downstream) side 154 of the cylindrical housing wall 135. Figure 6 The plurality of cooling channels 172 may include a first slotted cooling channel 174 extending at least partially in the circumferential direction 168 between a first lateral direction 144 of the flow axis 140 and a lateral direction 146, and a second slotted cooling channel 176 extending at least partially in the circumferential direction 168 between a second lateral direction 150 of the flow axis 140 and a lateral direction 146. Similarly, Figure 6 The aspect may include a third slotted cooling channel 178 extending at least partially in the circumferential direction 168 between a first lateral direction 144 of the flow axis 140 and a lateral direction 146, and a fourth slotted cooling channel 180 extending at least partially in the circumferential direction 168 between a second lateral direction 150 of the flow axis 140 and a lateral direction 146. Additionally, in Figure 6 In the image, it can be seen that each of the multiple cooling channels 172 includes a corresponding airflow inlet channel 156. (Reference) Figure 7 , Figure 7 Is Figure 6 The view Figure 7-7 A view of the igniter housing 102 taken from the rear to the front shows that each of the airflow inlet channels 156 is a slotted inlet channel 182 with a slot height 184 and a slot width 186. Similar to the circular inlet channel 158, the diameter is 160 (…). Figure 5 The dimensions of the slot height 184 and slot width 186 can be determined based on the amount of airflow required through the slotted cooling channel 172. Although Figure 6 Four slotted cooling channels 172 are depicted, but more than four slotted cooling channels 172 may be included alternatively. Furthermore, fewer than four slotted cooling channels 172 may be included. For example, a first slotted cooling channel 174 and a third slotted cooling channel 178 may be formed to define a single slotted cooling channel, and a second slotted cooling channel 176 and a fourth slotted cooling channel 180 may also be formed to define a single slotted cooling channel.

[0040] Figure 8 According to another aspect of this disclosure, similar to Figure 3 A partial cross-sectional view of the alternative ignition assembly to the ignition assembly. Figure 9 It is based on one aspect of this disclosure Figure 8 A cross-sectional view of the alternative igniter assembly taken at plane 9-9. (Common Reference) Figure 8 and 9 The second (downstream) side 154 of the igniter housing 102 and Figure 3 and 4 The similarity lies in that the second (downstream) side 154 includes an airflow inlet passage 156 and a cooling passage 162, wherein the airflow inlet passage 156 is defined as a circular inlet passage 158. Figure 5 Furthermore, cooling channel 162 is defined as slotted cooling channel 166. However, in Figure 8 and 9 In this respect, the first (upstream) side 152 of the cylindrical outer casing wall 135 includes at least one upstream cavity 188. The upstream cavity 188 may resemble the slotted cooling channel 166 and may itself be a slotted upstream cavity 190. At least one upstream cavity 188 is in fluid communication with the slotted cooling channel 166. That is, the upstream cavity 188 may receive airflow from the slotted cooling channel 166 and may provide return airflow to the slotted cooling channel 166.

[0041] The slotted upstream cavity 190 extends in the circumferential direction 168 within the outer casing wall 132, and as... Figure 8 and 9 As shown, it extends between a first lateral direction 148 and a second lateral direction 150. Furthermore, the slotted upstream cavity 190 extends along an axial length 192 of the housing wall 132 from a first end 194 to a second end 196 in the axial direction 138. The first end 194 and the second end 196 of the slotted upstream cavity 190 are defined within the housing wall 132, thereby defining a closed upstream cavity. Here, the term "closed cavity" may refer to a slotted upstream cavity that can receive cooling airflow from the slotted cooling passage 166 and can provide return cooling airflow to the slotted cooling passage 166, but the slotted upstream cavity 190 is axially closed at the first end 194 and closed at the second end 196, such that the cooling airflow within the slotted upstream cavity 190 is not provided through the inner end 120 of the igniter housing 102. The first end 194 may be located close to the inner end 120. In this embodiment, "close to" means that the first end 194 is not flush with the inner end 120, but is within a range of 25 to 50 millimeters of the inner end 120 of the igniter housing 102. Of course, the first end 194 can be located in other ranges of the inner end 120, and this disclosure is not limited to the above-described range.

[0042] Figure 10 It is similar to another aspect of this disclosure. Figure 3 A partial cross-sectional view of the alternative ignition assembly to the ignition assembly. Figure 11 It is based on one aspect of this disclosure Figure 10 A cross-sectional view of the alternative igniter assembly taken at plane 11-11. (Common Reference) Figure 10 and 11 The igniter housing 102 is similar to Figure 3 and 4 The description of the ignition housing 102 in these figures applies to the ignition housing. Figure 10 and 11 The igniter housing 102. However, in Figure 10 and 11 The image includes additional details of the igniter 104. The igniter 104 includes an electrode 198 extending through a shaft portion 200 disposed within the igniter housing 102. The electrode 198 may be surrounded by an insulator (not shown) between the electrode and the shaft portion 200, and may be coupled to an ignition source (not shown) to provide charge to the electrode 198. The shaft portion 200 has a first end 204 arranged close to the inner end 120 of the igniter housing 102. For this particular embodiment, "close to" may refer to being flush with the inner end 120, or within a given range (e.g., ±10 mm) of being flush with the inner end 120 of the igniter housing 102. The shaft portion 200 also includes a hollow, enclosed insulating cavity 202 located therein. The hollow, enclosed insulating cavity 202 is an enclosed cavity without an airflow inlet or outlet, and is arranged as an insulator for the igniter electrode 198. The hollow, enclosed insulating cavity 202 extends circumferentially around the centerline axis 206 of the shaft portion 200. The hollow, enclosed insulating cavity 202 has an axial length 208 that extends in the axial direction 138 relative to the centerline axis 206 of the shaft portion 202 from a first end 210 to a second end 212 of the hollow, enclosed insulating cavity 202. The first end 210 of the hollow, enclosed insulating cavity 202 may be arranged close to the first end 204 of the shaft portion 200, or within a given range. The second end 212 of the hollow, enclosed insulating cavity 202 may be arranged such that when the igniter 104 is disposed within the igniter housing 102 and the first end 204 of the igniter 104 is close to the inner end 120 of the igniter housing 102, the second end 212 is arranged close to at least one airflow inlet passage 156 of the igniter housing 102. Alternatively, the second end 212 of the hollow enclosed insulating cavity 202 may extend outward along the central axis 206 toward the outer shell 64 beyond the airflow inlet channel 156.

[0043] Figure 12 This is a partial cross-sectional view of an alternative igniter assembly according to another aspect of this disclosure. Figure 13 It is based on one aspect of this disclosure Figure 12 A cross-sectional view of the alternative igniter assembly taken at plane 13-13. Figure 12and 13 In this respect, the igniter assembly 75 does not include the igniter housing 102, but instead includes an igniter mounting adapter 214, on which the igniter 104 is mounted, and an igniter grommets 216 are configured to pass through an igniter opening 124 in the outer liner 54, wherein the igniter 104 extends through the igniter grommets 216. The igniter mounting adapter 214 can be connected to the adapter 106 via an external threaded portion 218, similar to reference [reference missing]. Figure 3 The connection between the igniter housing 102 and the adapter 106 is described. The igniter 104 can be connected to the igniter mounting adapter 214 via the internal thread 220 of the igniter mounting adapter 214, similar to... Figure 3 Igniter 104 is connected to igniter housing 102.

[0044] The ignition grommets 216 include a cold surface side 222 and a hot surface side 224. Similar to... Figure 3 A slotted cooling channel 166 and a cooling channel 226 are arranged on the downstream side 228 of the igniter ring 216 and extend from the cold surface side 222 through the igniter ring 216 to the hot surface side 224. The cooling channel 226 extends in the circumferential direction 168 about the central axis 234 of the igniter ring 216. The igniter ring 216 includes an igniter opening 230 extending therethrough, and the igniter 104 extends through the igniter opening 230. The implementation of the gasket 114 is similar to... Figure 3 In order to adjust the alignment of the inner end 232 of the igniter 104 with respect to the hot surface side 224 of the igniter grommets 216, the inner end 232 is arranged close to the hot surface side 224. In this embodiment, "close to" means flush with the hot surface 224, or within ±10 mm of being flush with the hot surface side 224. Of course, other ranges can be used instead, and this embodiment is not limited to the above range. Therefore, utilizing Figure 12 and 13 The arrangement of the cooling channel 226 allows the cooling airflow 82(c) to flow through it, thereby providing cooling to the downstream side 170 of the igniter opening 124 on the hot surface side 122 of the outer liner 54.

[0045] Figure 14 This is based on one aspect of the disclosure. Figure 13 A cross-sectional view of an alternative ignition swivel arrangement to the depicted ignition swivel arrangement. Figure 14 In the arrangement, the igniter grommets 216 include an igniter opening 230, which extends circumferentially around the central axis 234 of the igniter grommets 216 and from the cold surface side 222 of the igniter grommets 216. Figure 12 ) extends to the hot surface side 224 of the igniter grommets 216 ( Figure 12The cylindrical wall 236 of the igniter ring 216. On the downstream side 228 of the igniter ring 216, the cylindrical wall 236 includes a plurality of grooves 238 that define a plurality of vortex blades 240 between the respective grooves 238. That is, ridges formed between the respective grooves 238 form vortex blades 240. Figure 15 Is Figure 14 Rear view of the cylindrical wall 236, taken at plane 15-15, where the igniter 104 has been removed. (See image below.) Figure 15 As shown, each of the plurality of grooves 238, and the plurality of vortex blades 240, extend from the cold surface side 222 of the igniter ring 216 to the hot surface side 224. The vortex blades 240 may be arranged at a vortex blade angle 241 relative to the centerline axis 234 of the igniter ring 216. Although Figure 15 The vortex impeller 240 and groove 238 depicted appear linear, but the groove 238 and vortex impeller 240 can be curved or helical to form a rifling-like groove. Therefore, in the outer flow channel 88 ( Figure 2 Compressed air flowing in ) 82(b)( Figure 14 A portion of it can be passed through the igniter opening 230 ( Figure 14 It provides, and the vortex can be introduced into the cooling airflow 82(c) through the igniter opening 230 by the vortex impeller 204.

[0046] Figure 16 This is a cross-sectional view of an alternative igniter grommets arrangement according to another aspect of this disclosure. Figure 16 As can be seen, the cylindrical wall 236 of the igniter grommets 216 does not include the multiple grooves 238 and multiple vortex vanes 240. Instead, the vortex vanes are disposed in the shaft portion 200 of the igniter 104. Figure 16 As shown, on the downstream side 246 of the shaft portion 200, the outer surface 248 of the shaft portion 200 includes a plurality of grooves 242 that define a plurality of vortex impellers 244. Each of the vortex impellers 244 may be similar to vortex impeller 240 ( Figure 15 The vortex impeller is arranged at an angle 241. Additionally, the groove 242 and the vortex impeller 244 can extend along the axial length of the shaft portion 200 from the inner end 232 of the igniter 104. Figure 12 The vortex impeller 244 in the shaft portion 200 extends beyond the cold surface side 222 of the igniter cable ring 216 into the external flow channel 88, so that the vortex impeller 244 in the shaft portion 200 can introduce the vortex into the flow of the cooling airflow 82(c) through the igniter opening 230.

[0047] While the foregoing description generally pertains to gas turbine engines, gas turbine engines can be implemented in a variety of environments. For example, the engine can be implemented in aircraft, but it can also be implemented in non-aircraft applications, such as power plants, marine applications, or oil and gas production applications. Therefore, this disclosure is not limited to use in aircraft.

[0048] The aforementioned aspects of this disclosure provide a cooling airflow on the downstream side of the ignition opening to cool the hot surface side of the liner. As a result, the durability of the liner can be improved.

[0049] Further aspects of this disclosure are provided by the subject matter of the following clauses.

[0050] A combustor for a gas turbine, the combustor comprising: a combustor liner defining a combustion chamber; a housing surrounding the combustor liner and defining an external flow passage therebetween; an igniter housing extending through an igniter opening through the combustor liner and extending through the external flow passage, the igniter housing having an inner end disposed on a hot surface side of the combustor liner adjacent to the combustion chamber; and an igniter disposed within the igniter housing, wherein the igniter housing includes a housing wall defining a periphery of the igniter housing. The housing wall has an upstream side and a downstream side opposite to the upstream side, and the housing wall includes (a) at least one airflow inlet channel on the downstream side of the housing wall and disposed within the external flow channel, and (b) at least one cooling channel within the housing wall on the downstream side, the at least one cooling channel extending from the at least one airflow inlet channel along the length of the igniter housing and through the inner end of the igniter housing, the at least one cooling airflow channel being in fluid communication with the at least one airflow inlet channel.

[0051] The burner according to the foregoing clause further includes an insulating layer disposed between the igniter housing and the igniter.

[0052] According to any of the preceding clauses, the burner wherein the at least one cooling passage is arranged to provide a cooling airflow to the hot surface side of the burner liner on the downstream side of the igniter opening.

[0053] The burner according to any of the preceding clauses, wherein the igniter housing is coupled to the housing body, and the igniter housing extends through the igniter opening passing through the burner liner, having a predetermined gap therebetween.

[0054] The burner according to any of the preceding clauses, wherein the periphery of the igniter housing defines a circular periphery, and the igniter housing includes a cylindrical housing wall having an axial opening extending therethrough along a central axis of the cylindrical housing wall, the igniter being disposed within the axial opening.

[0055] The burner according to any of the preceding clauses, wherein the at least one airflow inlet passage comprises a plurality of inlet passages passing through the housing wall and providing fluid communication between the external flow passage and the at least one cooling passage.

[0056] The burner according to any of the preceding clauses, wherein the at least one cooling channel includes at least one slotted cooling channel that extends in a circumferential direction on the downstream side of the housing wall relative to the centerline axis of the housing wall.

[0057] The burner according to any of the preceding clauses, wherein the centerline axis defines an axial direction, the flow axis of the outer casing wall extends orthogonally to the centerline axis and defines an upstream direction and a downstream direction, and the transverse axis of the outer casing wall extends through the centerline axis and extends orthogonally to the flow axis and defines a first transverse direction and a second transverse direction, and the at least one slotted cooling channel extends between the first transverse direction of the transverse axis and the second transverse direction of the transverse axis.

[0058] The burner according to any of the preceding clauses, wherein the at least one slotted cooling channel includes a first slotted cooling channel and a second slotted cooling channel, the first slotted cooling channel extending in a circumferential direction between the downstream direction and the first transverse direction, and the second slotted cooling channel extending between the downstream direction and the second transverse direction.

[0059] The burner according to any of the preceding clauses, wherein the housing wall further includes at least one upstream cavity on the upstream side of the housing wall, the at least one upstream cavity being in fluid communication with the at least one slotted cooling channel.

[0060] The burner according to any of the preceding clauses, wherein the at least one upstream cavity is a slotted upstream cavity extending in the circumferential direction and extending between the first lateral direction and the second lateral direction.

[0061] The burner according to any one of the preceding clauses, wherein the at least one upstream cavity extends along the axial length of the housing wall from a first end of the at least one upstream cavity to a second end of the at least one upstream cavity in the axial direction, the first end of the at least one upstream cavity and the second end of the at least one upstream cavity being defined within the housing wall.

[0062] The burner according to any of the preceding clauses, wherein the igniter includes a shaft portion disposed within the igniter housing, the shaft portion having a first end disposed near the inner end of the igniter housing, and the shaft portion including a hollow, closed, insulating cavity located therein.

[0063] The burner according to any of the preceding clauses, wherein the hollow enclosed insulating cavity extends circumferentially around the centerline axis of the shaft portion and has an axial length relative to the centerline axis of the shaft portion extending from a first end of the hollow enclosed insulating cavity to a second end of the hollow enclosed insulating cavity in the axial direction.

[0064] According to any of the preceding clauses, the first end of the hollow enclosed insulating cavity is arranged near the first end of the shaft portion, and the second end of the hollow enclosed insulating cavity is arranged such that when the igniter is disposed within the igniter housing and the first end of the shaft portion is near the inner end of the igniter housing, the second end is arranged near the at least one airflow inlet passage of the igniter housing.

[0065] The burner according to any of the preceding clauses, wherein the burner liner includes an outer liner extending circumferentially around the burner centerline axis and an inner liner extending circumferentially around the burner centerline axis, the combustion chamber is defined between the outer liner and the inner liner, and the outer flow channel is defined around the outer liner and between the outer liner and the outer flow channel, and the igniter housing extends through the outer liner and through the outer flow channel.

[0066] The burner according to any of the preceding clauses, wherein the outer liner includes a housing and a heat insulation plate, the heat insulation plate being connected to the housing to define a baffle cavity therebetween, and the hot surface side of the burner liner includes the hot surface side of the heat insulation plate.

[0067] A gas turbine includes: a compressor section; and a combustor, the compressor section providing a compressed air flow to the combustor, the combustor including: a combustor liner defining a combustion chamber; at least one vortex assembly providing the compressed air flow and fuel to the combustion chamber as a fuel-air mixture; a housing surrounding the combustor liner and defining an external flow passage therebetween, at least a portion of the compressed air flow being directed through the external flow passage; an igniter housing extending through an igniter opening through the combustor liner and extending through the external flow passage, the igniter housing having an inner end disposed on a hot surface side of the combustor liner adjacent to the combustion chamber; and an igniter. The igniter is disposed within the igniter housing to ignite the fuel-air mixture, wherein the igniter housing includes a housing wall defining a periphery of the igniter housing, the housing wall having an upstream side and a downstream side opposite to the upstream side, and the housing wall including (a) at least one airflow inlet passage on the downstream side of the housing wall and disposed within the external flow passage, and (b) at least one cooling passage within the housing wall on the downstream side, the at least one cooling passage extending from the at least one airflow inlet passage along the length of the igniter housing and through the inner end of the igniter housing, the at least one cooling airflow passage being in fluid communication with the at least one airflow inlet passage.

[0068] According to the gas turbine of the foregoing clause, wherein the igniter operates to ignite the fuel-air mixture in the combustion chamber, and the at least one cooling passage in the igniter housing provides a compressed air flow from the external flow passage passing through it to provide a cooling airflow from the hot surface side of the burner liner to the downstream side of the igniter opening passing through the burner liner.

[0069] According to any of the preceding clauses, the gas turbine, wherein the igniter housing includes a cylindrical housing wall, the at least one cooling passage includes at least one slotted cooling passage extending circumferentially within the cylindrical housing wall on the downstream side, the cylindrical housing wall further including at least one upstream cavity on the upstream side of the housing wall, the at least one upstream cavity being in fluid communication with the at least one slotted cooling passage and providing impingement cooling to the upstream side of the igniter housing.

[0070] The gas turbine according to the foregoing clause further includes an insulating layer disposed between the igniter housing and the igniter.

[0071] According to any of the preceding clauses, the gas turbine wherein the at least one cooling passage is arranged to provide a cooling airflow to the hot surface side of the burner liner on the downstream side of the igniter opening.

[0072] According to any of the preceding clauses, the gas turbine, wherein the igniter housing is configured to be coupled to the housing body, and the igniter housing extends through the igniter opening through the burner liner, having a predetermined gap therebetween.

[0073] According to any of the preceding clauses, the gas turbine wherein the periphery of the igniter housing defines a circular periphery, and the igniter housing includes a cylindrical housing wall having an axial opening extending therethrough along a central axis of the cylindrical housing wall, the igniter being disposed within the axial opening.

[0074] According to any of the preceding clauses, the gas turbine comprises a plurality of inlet passages passing through the cylindrical outer casing wall and providing fluid communication between the external flow passage and the at least one cooling passage.

[0075] According to any of the preceding clauses, the gas turbine comprises at least one slotted cooling channel that extends circumferentially on a second side of the housing wall relative to the centerline axis of the housing wall.

[0076] According to any of the preceding clauses, the gas turbine, wherein the centerline axis defines an axial direction, the flow axis of the cylindrical outer casing extends orthogonally to the centerline axis and defines an upstream direction and a downstream direction, and the transverse axis of the cylindrical outer casing extends through the centerline axis and extends orthogonally to the flow axis and defines a first transverse direction and a second transverse direction, and the at least one slotted cooling channel extends between the first transverse direction of the transverse axis and the second transverse direction of the transverse axis.

[0077] The gas turbine according to any one of the preceding clauses, wherein the at least one slotted cooling channel includes a first slotted cooling channel and a second slotted cooling channel, the first slotted cooling channel extending in a circumferential direction between the downstream direction and the first transverse direction, and the second slotted cooling channel extending between the downstream direction and the second transverse direction.

[0078] According to any of the preceding clauses, the gas turbine further includes at least one upstream cavity on the first side of the outer casing wall, the at least one upstream cavity being in fluid communication with the at least one slotted cooling channel.

[0079] According to any of the preceding clauses, the gas turbine is wherein the at least one upstream cavity is a slotted upstream cavity extending in the circumferential direction and extending between the first lateral direction and the second lateral direction.

[0080] According to any of the preceding clauses, the gas turbine wherein the at least one upstream cavity extends along the axial length of the cylindrical housing wall from a first end of the at least one upstream cavity to a second end of the at least one upstream cavity in the axial direction, the first end of the at least one upstream cavity and the second end of the at least one upstream cavity being defined within the cylindrical housing wall.

[0081] According to any of the preceding clauses, the gas turbine, wherein the igniter includes a shaft portion disposed within the igniter housing, the shaft portion having a first end disposed near the inner end of the igniter housing, and the shaft portion including a hollow, enclosed, insulating cavity therein.

[0082] According to any of the preceding clauses, the gas turbine, wherein the hollow enclosed insulating cavity extends circumferentially around the centerline axis of the shaft portion and has an axial length relative to the centerline axis of the shaft portion extending from a first end of the hollow enclosed insulating cavity to a second end of the hollow enclosed insulating cavity in the axial direction.

[0083] According to any of the preceding clauses, the first end of the hollow enclosed insulating cavity is arranged near the first end of the shaft portion, and the second end of the hollow enclosed insulating cavity is arranged such that when the igniter is disposed within the igniter housing and the first end of the shaft portion is near the inner end of the igniter housing, the second end is arranged near the at least one airflow inlet passage of the igniter housing.

[0084] According to any of the preceding clauses, the gas turbine comprises an outer liner extending circumferentially around a burner centerline axis and an inner liner extending circumferentially around the burner centerline axis, the combustion chamber being defined between the outer liner and the inner liner, and the outer flow passage surrounding the outer liner and defined between the outer liner and the outer liner, and the igniter housing extending through the outer liner and extending through the outer flow passage.

[0085] According to any of the preceding clauses, the gas turbine liner includes an outer shell and a heat shield, the heat shield being connected to the outer shell to define a baffle cavity therebetween, and the hot surface side of the burner liner includes the hot surface side of the heat shield.

[0086] While the foregoing description is directed to some exemplary embodiments of the present disclosure, other changes and modifications will be apparent to those skilled in the art and can be made without departing from the spirit or scope of the present disclosure. Furthermore, features described in connection with one embodiment of the present disclosure may be used in conjunction with other embodiments, even if not explicitly stated above.

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