Dome-guide joint cooling arrangement

Abstract

A dome - guide vane assembly for a gas turbine comprising a dome, a guide vane and at least one dome - guide vane connection assembly comprising a connection member connecting the dome and the guide vane together and a cavity defined between the dome and the guide vane. The connection member extends through the guide vane and has a first end arranged at a hot surface side of the guide vane and a second end arranged in connection with the dome. The dome - guide vane connection assembly is configured to provide a flow of cooling air from the cavity to the hot surface side of the guide vane to cool the first end of the connection member at the hot surface side of the guide vane.

Description

TECHNICAL FIELD

[0001] The present disclosure relates generally to a dome-to-duct connection in a combustor in a gas turbine. BACKGROUND

[0002] Some gas turbine engines include combustors having a dome to which a duct is connected. The duct can be connected to the dome by bolting to the dome. The heads of the bolts can be typically arranged on the combustion chamber side of the duct. As a result, the bolt joints, and more particularly the bolt heads, are exposed to intense heat from combustion within the combustor. 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 refer to like elements, functionally similar and / or structurally similar elements, and in which:

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

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

[0006] Figure 3 is a detailed view of a dome-to-duct connection assembly according to one aspect of the present disclosure taken at Figure 2 is a schematic partial cross-sectional view of a dome-to-duct connection assembly according to one aspect of the present disclosure taken at

[0007] Figure 4 depicts an arrangement of duct cooling passages around a duct side connection member opening according to one aspect of the present disclosure taken at Figure 3 is a detailed view of a dome-to-duct connection assembly according to another aspect of the present disclosure taken at Figures 4-4

[0008] Figure 5 is a cross-sectional view according to one aspect of the present disclosure taken at plane 5-5 of Figure 3

[0009] is a schematic partial cross-sectional view of a dome-to-duct assembly according to another aspect of the present disclosure taken at Figure 6 Figure 2

[0010] Figure 7A depicts an arrangement of duct cooling passages around a duct side connection member opening according to one aspect of the present disclosure taken at Figure 6

[0011] Figure 7B depicts an arrangement of duct cooling passages around a duct side connection member opening according to another aspect of the present disclosure taken at​​​​Figure 6 The arrangement of the coolant channels around the opening of the flow guide side connecting member, as shown in view 7-7.

[0012] Figure 8 It is based on one aspect of this disclosure. Figure 6 A partial cross-sectional view taken from plane 8-8, passing through a portion of the hollow conical truncated sleeve.

[0013] Figure 9 It is based on another aspect of this disclosure. Figure 2 A schematic partial cross-sectional view of the dome-guide assembly, taken at 100 degrees.

[0014] Figure 10 It is based on one aspect of this disclosure. Figure 9 The view Figures 10-10 A top view of the hollow conical truncated sleeve taken at the point. Detailed Implementation

[0015] The features, advantages, and embodiments of this disclosure will be set forth or apparent from consideration of the following detailed description, accompanying 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.

[0016] 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 constructions can be used without departing from the spirit and scope of this disclosure.

[0017] As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the components.

[0018] 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.

[0019] Some gas turbine engines include a combustor with a dome, to which a diffuser is connected. The diffuser can be bolted to the dome. The head of the bolt is typically positioned on the combustion chamber side of the diffuser. As a result, the bolt joint, more specifically, the bolt head, is exposed to intense heat from combustion within the combustor. Over time, the high temperatures can damage the structural integrity of the bolt head, necessitating bolt replacement.

[0020] The present disclosure provides a technique for connecting a dome and a flow director in order to provide a cooling airflow to a bolt head. More specifically, in the present disclosure, various arrangements provide for directing cooling air flowing into a cavity between the dome and the flow director toward the bolt head on the combustion chamber side of the flow director, thereby providing cooling to the bolt head. By providing cooling to the bolt head, the life of the bolt can be extended, thereby reducing the need for replacement.

[0021] Reference will now be made to the drawings, Figure 1 is a schematic partial cross-sectional side view of an exemplary high-bypass turbofan jet engine 10, referred to herein as "engine 10," which can incorporate various embodiments of the present disclosure. Although further described below with reference to a turbofan engine, the present invention is also applicable to turbine engines in general, including turbojet, turboprop, and turboshaft gas turbine engines, including marine turbine engines, industrial turbine engines, and auxiliary power units. As Figure 1 shown, engine 10 has an axial centerline axis 12 extending 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 arranged downstream of fan assembly 14.

[0022] Core engine 16 can generally include an outer casing 18 defining an annular inlet 20. Outer casing 18 surrounds or at least partially forms, in serial flow relationship, a compressor section (22 / 24) having a low pressure (LP) compressor 22 and a high pressure (HP) compressor 24, a combustor 26, a turbine section (28 / 30) including a high pressure (HP) turbine 28 and a low pressure (LP) turbine 30, and 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, LP rotor shaft 36 can be connected to fan shaft 38 through a reduction gear 40, for example, in an indirect drive or geared drive configuration.

[0023] As Figure 1 shown, fan assembly 14 includes a plurality of fan blades 42 connected 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.

[0024] Figure 2 is an exemplary combustor 26 of the core engine 16 as Figure 1 shown. As Figure 2 shown, the combustor 26 can generally include a combustor inner liner 50 having an inner liner 52 and an outer liner 54, and a dome assembly 56, which together define a combustion chamber 62. Both the inner liner 52 and the outer liner 54 can extend circumferentially about a combustor centerline axis 13, which can correspond to the engine axial centerline axis 12. The inner liner 52 and the outer liner 54 are connected to a fairing 60, and a plenum 66 is defined between the fairing 60, the inner liner 52, the outer liner 54, and the dome assembly 56. The 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, multiple mixer assemblies 58 and corresponding fuel nozzle assemblies 70 can be included in the combustor 26, with each corresponding mixer assembly 58 and fuel nozzle assembly 70 circumferentially spaced apart about the combustor centerline axis 13.

[0025] As Figure 2 shown, the inner liner 52 is housed within an inner housing 65, and the outer liner 54 is housed within an 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 combustor centerline axis 13. The inner liner 52 and the outer liner 54 can extend from the dome assembly 56 to turbine nozzles 79 at an inlet of the HP turbine 28 Figure 1 ), thus at least partially defining a hot gas path between the combustor liner 50 and the HP turbine 28. The 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 recirculation of the combustion gases 86 can occur at the primary combustion zone 74 before the combustion gases 86 flow further downstream within the combustion chamber 62 and into the turbine nozzles 79 at an inlet of the HP turbine 28 and the LP turbine 30. The outer liner 54 can be a multi-layered inner liner including an outer liner shell 53 and outer liner plates 55 connected to the outer liner shell 53 by a plurality of outer liner shell-plate connection members 57. Similarly, the inner liner 52 can be a multi-layered inner liner including an inner liner shell 59 and inner liner plates 61 connected to the inner liner shell 59 by a plurality of inner liner shell-plate connection members 63. Further, as will be described in greater detail below, the dome assembly 56 can include a dome 67 and a flow inducer 68 connected to the dome 67 by a dome-to-flow inducer connection member 71.

[0026] During operation of the engine 10, asFigure 1 and Figure 2 As shown, a certain volume of air, schematically indicated by arrow 73, 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 guided as a bypass airflow 78 into the bypass airflow passage 48, while another portion of the air 73 is directed or guided into the LP compressor 22 as compressor inlet air 80. 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 2 As shown, compressed air 82 flows into and pressurizes the diffuser chamber 84. A first portion of the compressed air 82, schematically indicated by arrow 82(a), flows from the diffuser chamber 84 into the pressure chamber 66, where it is mixed with fuel supplied by the fuel nozzle assembly 70 via the mixer assembly 58. The fuel-oxidizer mixture 72 is then injected by the mixer assembly 58 into the combustion chamber 62. The fuel-oxidizer mixture 72 is ignited and burned by the igniter 75 to produce combustion gases 86 within the main combustion zone 74 of the combustion chamber 62. 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. Furthermore, or alternatively, at least a portion of the compressed air 82(b) can be drawn 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.

[0027] Refer again Figure 1 and Figure 2 The combustion gases 86 generated in combustion chamber 62 flow through turbine nozzle 79 and enter HP turbine 28, causing HP rotor shaft 34 to rotate, thereby supporting the operation of 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 jet exhaust nozzle section 32 of the core engine 16 to provide propulsion at the downstream end 99.

[0028] Figure 3 It is based on one aspect of this disclosure. Figure 2 A schematic partial cross-sectional view of the dome-guide assembly 101, taken at detail view 100. (See attached image.) Figure 3As shown, dome 67 and diffuser 68 are connected together via dome-diffuser connection assembly 102. Figure 3 In this respect, the dome-guide connection assembly 102 includes a connecting member 104, which in Figure 3 The bolt 106 is in the form of a bolt 106. A dome 67 and a diffuser 68 are interconnected to define a cavity 116 between the dome 67 and the diffuser 68. The dome 67 includes a dome-side connecting member opening 108 and may include a plurality of dome cooling channels 111 extending from an upstream side 113 of the dome 67 through the dome 67 to a cavity side 115 of the dome 67. The dome cooling channels 111 provide a flow of compressed air 82(b) to flow from a pressure chamber 66 on the upstream side 113 of the dome 67 into the cavity 116. The diffuser 68 includes a diffuser-side connecting member opening 110 extending from a cold surface side 112 of the diffuser 68 to a hot surface side 114 of the diffuser 68. The bolt 106 (connecting member 104) includes a first end 118 defining a bolt head 120 and a second end 122 defining a threaded shank portion 124. The bolt head 120 engages with the hot surface side 114 of the guide vane, and, as Figure 3 As shown, the diffuser-side connecting member opening 110 can be countersunk at the hot surface side 114 to allow the bolt head 120 to be flush with the hot surface side 114 of the diffuser 68. The bolt 106 (connecting member 104) extends through the diffuser-side connecting member opening 110 and through the dome-side connecting member opening 108. The threaded shank portion 124 can be threadedly engaged with the retaining member 126 (e.g., a nut).

[0029] The dome-guide connector assembly 102 is configured to provide a cooling fluid flow from the upstream side 113 of the dome 67 adjacent to the pressure chamber 66 and from the cavity 116 to the hot surface side 114 of the guide vane 68, to cool the first end 118 of the connector member 104 of the hot surface side 114 of the guide vane 68. Figure 3 In this respect, bolt 106 includes a shank 128 extending between a first end 118 and a second end 122. A plurality of longitudinally slotted cooling channels 130 are arranged to pass through the outer surface 132 of bolt 106 and extend along at least a portion of the shank 128 and through bolt head 120. Figure 3 The view Figures 4-4 Cut off Figure 4 A view depicting a longitudinally slotted cooling channel 130 extending through the bolt head 120 at the hot surface side 114 of the diffuser 68 is shown. Thus, the plurality of longitudinally slotted cooling channels 130 provide airflow 82(c) to flow from the upstream side 113 of the dome 67 and from the cavity 116 to the hot surface side 114 of the diffuser 68 and to provide cooling for the bolt head 120.

[0030] Still referencing Figure 3The dome-guide connector assembly 102 may also include a sleeve 134 that engages with the shank 128 of the bolt 106 on the upstream side 113 of the dome 67. To provide a cooling airflow 82(c) to the longitudinally slotted cooling channels 130, the sleeve 134 may include a plurality of sleeve cooling channels 136 that provide fluid communication with the plurality of longitudinally slotted cooling channels 130 of the bolt 106. The sleeve cooling channels 136 may generally be arranged orthogonally to the slotted cooling channels 130, or they may be angled to define a generally helical arrangement, such that the sleeve 134 is arranged as a spring-like sleeve.

[0031] Figure 3 The dome-guide connector assembly 102 may also include a bell sleeve 138. The bell sleeve 138 engages with the upstream side 113 of the dome 67. (Reference) Figure 5 It is in Figure 3 A cross-sectional view taken from plane 5-5 shows that the bell sleeve 138 includes a sleeve opening 140 passing through it, and the bolt 106 extends through the sleeve opening 140. Furthermore, the bell sleeve 138 may include a plurality of cooling channels 142 passing through it. The cooling channels 142 allow compressed air 82(b) from the pressure chamber 66 to flow through them, thereby providing air 82(c) to the plurality of longitudinally slotted cooling channels 130 of the bolt 106. Figure 3 The aspect may also include a spring washer 145 disposed between the upstream side 113 of the dome 67 and the sleeve 134.

[0032] Figure 6 It is based on another aspect of this disclosure. Figure 2 A schematic partial cross-sectional view of the dome-guide assembly 101, taken at detail view 100. Figure 6 In this respect, the dome-guide connector assembly 102 includes a bolt 144 as a connecting member 104, wherein the first end 146 of the bolt 144 includes a connector with... Figure 3 The bolt head 120 is similar to the bolt head 150. The bolt 144 also includes a second end 148, which is similar to... Figure 3 The second end 122 of the bolt 106 includes a threaded shank portion 152 that threadedly engages with a retaining member 126 in the form of a nut. Furthermore, similar to... Figure 3 In terms of the dome 67, the dome 67 includes a dome-side connecting member opening 108, and the flow guide 68 includes a flow guide-side connecting member opening 110. The dome 67 also includes a plurality of dome cooling channels 111 extending therethrough.

[0033] exist Figure 6In aspects of the disclosure, the flow director 68 includes a plurality of flow director cooling passages 154 extending therethrough and disposed adjacent the flow director side connector member opening 110 so as to provide a flow of air 82(c) from the cavity 116 to cool the bolt head 150. In one aspect, the flow director cooling passages 154 can be disposed at an angle 156 so as to direct the flow of air 82(c) toward the bolt head 150. The angle 156 can have a range of, for example, from forty-five degrees to seventy degrees, although the angle 156 is not limited to the foregoing range and can instead implement other angles.

[0034] Figure 7A and 7B depicts the arrangement of the flow director cooling passages 154 around the flow director side connector member opening 110. Figure 7A and Figure 7B are taken from Figure 6 view 7-7 in Figure 7A , it can be seen that the plurality of flow director cooling passages 154 are arranged in a plurality of circumferential rows around the flow director side connector member opening 110, including a first circumferential row 158 and a second circumferential row 160. In Figure 7A , it can be seen that the plurality of flow director cooling passages 154 in the first circumferential row 158 are radially aligned with a corresponding one of the plurality of flow director cooling passages 154 in the second circumferential row 160 along a radial line 162 extending outwardly from a centerline axis 164 of the flow director side connector member opening 110. In Figure 7B , it can be seen that the plurality of flow director cooling passages 154 in the first circumferential row 158 can be circumferentially offset from the corresponding flow director cooling passages 154 in the second circumferential row 160. For example, the flow director cooling passages 154 of the first circumferential row 158 can be aligned along the radial line 162, while the flow director cooling passages 154 in the second circumferential row 160 can be aligned along a radial line 166 having an offset angle 168 from the radial line 162.

[0035] Referring back to Figure 6 , the dome-flow director connection assembly includes a hollow conical frustum sleeve 170 disposed within the cavity 116 and around the bolt 144 (connector member 104) to define a sleeve cavity 178 therein. The dome cooling passage 111 provides a flow of compressed air 82(b) from the pressure plenum 66 into the sleeve cavity 178. In Figure 6In this arrangement, the small-diameter end 172 of the hollow conical truncated sleeve 170 engages with the cavity side 115 of the dome 67, and the large-diameter end 174 engages with the cold surface side 112 of the guide vane 68. In an alternative arrangement, a converging hollow conical truncated sleeve 176 can be implemented, such that the small-diameter end 172 engages with the cold surface side 112 of the guide vane 68, and the large-diameter end 174 engages with the cavity side 115 of the dome 67. The converging hollow conical truncated sleeve 176 can provide a converging flow of compressed air 82(b) through the sleeve cavity 178, thereby increasing the pressure of the airflow leaving the guide vane cooling passage 154.

[0036] To maintain the positioning of the hollow conical truncated sleeve 170 between the dome 67 and the flow deflector 68, the flow deflector 68 may include a plurality of sleeve support members 180 extending from the cold surface side 112 of the flow deflector 68. The sleeve support members 180 may be integrally formed with the flow deflector 68. As an alternative holding method, the hollow conical truncated sleeve 170 may be integrally formed with the dome 67 or with the flow deflector 68, or may be bonded to the dome 67 or the flow deflector 68 by, for example, brazing.

[0037] Figure 8 It is along Figure 6 A partial cross-sectional view taken from plane 8-8 through a portion of the hollow conical truncated sleeve 170 or through the converging hollow conical truncated sleeve 176. (See also...) Figure 8 As seen, the inner surface 182 of the hollow conical truncated sleeve 170 may include a plurality of grooves 184 and / or a plurality of ribs 186. The plurality of grooves 184 and / or the plurality of ribs 186 may extend around the entire circumference of the inner surface of the hollow conical truncated sleeve 170. The plurality of grooves 184 and / or the plurality of ribs 186 may also extend along the entire length of the inner surface 182 from the small diameter end 172 to the large diameter end 174, or may extend only partially along the length of the inner surface 182 between the small diameter end 172 and the large diameter end 174.

[0038] Figure 9 It is based on another aspect of this disclosure. Figure 2 A schematic partial cross-sectional view of the dome-guide assembly 101 taken at detail view 100. Figure 9 Similar to Figure 6 In this respect, but including hollow conical truncated sleeve 188, which differs from hollow conical truncated sleeve 170 and converging hollow conical truncated sleeve 176. Figure 9In the embodiment, the hollow conical frustum sleeve 188 includes a frustoconical outer wall 190 having a large diameter end 192 and a small diameter end 194, and a cylindrical inner wall 196 having a connection member opening 198 extending from a first end 200 of the cylindrical inner wall 196 to a second end 202 of the cylindrical inner wall 196. A sleeve cavity 204 is defined between the cylindrical inner wall 196 and the frustoconical outer wall 190. At least one base connection member 206 connects the large diameter end 192 of the frustoconical outer wall 190 and the first end 200 of the cylindrical inner wall 196, and at least one top connection member 208 connects the small diameter end 194 of the frustoconical outer wall 190 and the second end 202 of the cylindrical inner wall 196.

[0039] Figure 10 is a top view of the hollow conical frustum sleeve 188 taken at the plane of the line Figure 9 Figures 10-10 is a top view of the hollow conical frustum sleeve 188 taken at the plane of the line Figure 10 In the embodiment, the top connection member 208 can be a circular plate 210 connected to the small diameter end 194 of the frustoconical outer wall 190 and also connected to the second end 202 of the cylindrical inner wall 196. To provide a flow of compressed air 82(b) into the sleeve cavity 204, the circular plate 210 can include a plurality of air flow openings 212 therethrough arranged in alignment with the dome cooling passages 111 through the dome 67. Alternatively, in addition to including the circular plate 210 with air flow openings 212, a plurality of spoke-type connectors 214 can be implemented to connect the small diameter end 194 of the frustoconical outer wall 190 and the second end 202 of the cylindrical inner wall 196. The at least one base member 206 Figure 9 ) can include a similar arrangement to that of the circular plate 210 with air flow openings 213 therethrough, or can include a plurality of spoke-type connectors (not shown) similar to the spoke-type connectors 214 to connect the large diameter end 192 of the frustoconical outer wall 190 and the first end 200 of the cylindrical inner wall 196.

[0040] While the foregoing description generally relates to a gas turbine engine, the gas turbine engine can be implemented in various environments. For example, the engine can be implemented in an aircraft, but can also be implemented in non-aircraft applications, such as power generation stations, marine applications, or oil and gas production applications. Accordingly, the present disclosure is not limited to use in an aircraft.

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

[0042] ​A dome assembly for a gas turbine, the dome assembly comprising: a dome having a dome-side connection member opening; a flow guide having a cold surface side and a hot surface side and having a flow guide-side connection member opening therethrough extending from the cold surface side to the hot surface side; and at least one dome-flow guide connection assembly comprising a connection member connecting the dome and the flow guide together defining a cavity therebetween, the connection member extending through the flow guide-side connection member opening and comprising a first end disposed at the hot surface side of the flow guide and a second end disposed in connection with the dome at the dome-side connection member opening, wherein the dome-flow guide connection assembly is configured to provide a flow of cooling air from the cavity to the hot surface side of the flow guide to cool the first end of the connection member at the hot surface side of the flow guide.

[0043] The dome-flow guide assembly according to any of the preceding clauses, wherein the connection member comprises a bolt having a shank and a bolt head, the bolt head comprising the first end of the connection member, the bolt having a plurality of longitudinally slotted cooling channels disposed on an outer surface of the bolt and extending along at least a portion of the shank and through the bolt head.

[0044] The dome-flow guide assembly according to any of the preceding clauses, wherein the dome-flow guide connection assembly comprises a sleeve engaged with the shank of the bolt, the sleeve comprising a plurality of sleeve cooling channels therethrough providing fluid communication with the plurality of longitudinally slotted cooling channels of the bolt.

[0045] The dome-flow guide assembly according to any of the preceding clauses, wherein the dome-flow guide connection assembly further comprises a bell-shaped sleeve engaged with the dome, the bell-shaped sleeve comprising a plurality of cooling channels therethrough.

[0046] The dome-flow guide assembly according to any of the preceding clauses, wherein the dome-flow guide connection assembly further comprises a spring washer disposed between the dome and the sleeve.

[0047] The dome-flow guide assembly according to any of the preceding clauses, wherein the bolt further extends through the dome-side connection member opening and a retaining member is connected to the shank to connect the dome and the flow guide.

[0048] The dome-flow guide assembly according to any of the preceding clauses, wherein the flow guide comprises a plurality of flow guide cooling channels therethrough disposed proximate the flow guide-side connection member opening.

[0049] The dome-duct assembly of any of the preceding clauses, wherein the dome-duct connection assembly comprises a hollow conical frustum sleeve disposed within the cavity and around the connection member.

[0050] The dome-duct assembly of any of the preceding clauses, wherein the dome comprises a plurality of dome cooling channels therethrough arranged to provide a cooling air flow through the dome and into a sleeve cavity within the hollow conical frustum sleeve.

[0051] The dome-duct assembly of any of the preceding clauses, wherein the plurality of duct cooling channels are arranged at an angle to direct the cooling air flow from the sleeve cavity toward a centerline axis of the duct side connection member opening.

[0052] The dome-duct assembly of any of the preceding clauses, wherein a small diameter end of the hollow conical frustum sleeve is engaged with the dome and a large diameter end of the hollow conical frustum sleeve is engaged with the cold surface side of the duct.

[0053] The dome-duct assembly of any of the preceding clauses, wherein the hollow conical frustum sleeve is integrally formed with the dome.

[0054] The dome-duct assembly of any of the preceding clauses, wherein the duct comprises at least one sleeve support member arranged at the cold surface side of the duct and the at least one sleeve support member is engaged with the hollow conical frustum sleeve.

[0055] The dome-duct assembly of any of the preceding clauses, wherein the connection member further extends through the dome side connection member opening and a retention member is connected to the second end of the connection member.

[0056] The dome-duct assembly of any of the preceding clauses, wherein a large diameter end of the hollow conical frustum sleeve is engaged with the dome and a small diameter end of the hollow frustum conical sleeve is engaged with the cold surface side of the duct.

[0057] The dome-duct assembly of any of the preceding clauses, wherein the hollow conical frustum sleeve comprises a plurality of ribs and / or a plurality of grooves extending along an inner surface of the hollow conical frustum sleeve between the small diameter end and the large diameter end.

[0058] The dome-duct assembly of any of the preceding clauses, wherein the dome-duct connection assembly comprises a hollow conic frustum sleeve comprising (a) a frustoconical outer wall having a large diameter end and a small diameter end; (b) a cylindrical inner wall having a connection member opening extending from a first end of the cylindrical inner wall to a second end of the cylindrical inner wall, the cylindrical inner wall and the frustoconical outer wall defining a sleeve cavity therebetween; (c) at least one base connection member connecting the large diameter end of the frustoconical outer wall and the first end of the cylindrical inner wall; and (d) at least one top connection member connecting the small diameter end of the frustoconical outer wall and the second end of the cylindrical inner wall.

[0059] The dome-duct assembly of any of the preceding clauses, wherein the dome comprises a plurality of dome cooling channels therethrough arranged to provide a cooling air flow therethrough into the sleeve cavity.

[0060] The dome-duct assembly of any of the preceding clauses, wherein the plurality of duct cooling channels are arranged at an angle to direct cooling air flow from the sleeve cavity toward a centerline axis of the duct side connection member opening.

[0061] The dome-duct assembly of any of the preceding clauses, wherein the connection member further extends through the dome side connection member opening and a retention member is connected to the second end of the connection member.

[0062] While the foregoing description has been directed to some exemplary embodiments of the present disclosure, 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 conjunction with one embodiment can be used with other embodiments, even if not explicitly stated above.

Claims

1. A dome assembly for a gas turbine, characterized by, The dome assembly comprises: a dome having a dome-side connection member opening and a plurality of dome cooling channels extending through the dome and disposed about the dome-side connection member opening; a flow director having a cold surface side and a hot surface side and having a flow director-side connection member opening therethrough extending from the cold surface side to the hot surface side; and at least one dome-flow director connection assembly comprising (a) a bolt connecting the dome and the flow director together defining a dome-flow director cavity therebetween, the bolt extending through the flow director-side connection member opening and including a bolt head disposed at the hot surface side of the flow director, the bolt having a threadless shank connected to the bolt head and having a plurality of longitudinally slotted cooling channels disposed on an outer surface of the threadless shank and extending through the bolt head, and (b) a bell-shaped sleeve engaged with an upstream side of the dome, a pressure plenum being located at the upstream side of the dome, the bell-shaped sleeve having a first end engaged with the bolt and a second end engaged with the dome, the bell-shaped sleeve defining a sleeve-dome cavity between the bell-shaped sleeve and the dome, the plurality of dome cooling channels providing fluid communication between the sleeve-dome cavity and the dome-flow director cavity, and the bell-shaped sleeve including a plurality of bell-shaped sleeve cooling channels therethrough providing fluid communication from the pressure plenum through the bell-shaped sleeve into the sleeve-dome cavity, wherein the dome-flow director connection assembly is configured to provide a flow of cooling air from the plenum to the sleeve-dome cavity via the plurality of bell-shaped sleeve cooling channels, and to provide a flow of cooling air from the sleeve-dome cavity to the dome-flow director cavity via the plurality of dome cooling channels, and to provide a flow of cooling air from the dome-flow director cavity to the bolt head at the hot surface side of the flow director via the plurality of longitudinally slotted cooling channels to cool the bolt head at the hot surface side of the flow director.

2. Dome assembly for a gas turbine according to claim 1, characterized in that wherein the dome-flow director connection assembly further comprises a sleeve engaged with the threadless shank of the bolt and disposed between the dome and the bell-shaped sleeve, the sleeve including a plurality of sleeve cooling channels therethrough providing fluid communication from the sleeve-dome cavity to the plurality of longitudinally slotted cooling channels.

3. Dome assembly for a gas turbine according to claim 2, characterized in that wherein the dome-flow director connection assembly further comprises a spring washer disposed between the dome and the sleeve.

4. The dome assembly for a gas turbine according to claim 3, characterized in that, wherein the bolt further extends through the dome-side connection member opening and through the first end of the bell-shaped sleeve, the bolt further including a threaded shank, and a retaining member connected to the threaded shank to connect the dome and the flow director.

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