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公开(公告)号：US12071855B2
公开(公告)日：2024-08-27
申请号：US17976465
申请日：2022-10-28
发明人： Krzysztof Kowiel
CPC分类号： F01D25/04 , F01D9/065 , F01D25/30 , F16F1/3835 , F16F1/3842 , F05D2230/642 , F05D2250/40 , F05D2260/31 , F05D2260/96 , F16F2224/0225
摘要： An assembly is provided for a gas turbine engine. This engine assembly includes a gas turbine engine case, a conduit and a bushing. The gas turbine engine case includes a case wall and a boss at a port through the case wall. The conduit extends longitudinally along a centerline through the port and into an interior of the gas turbine engine case. The bushing circumscribes the conduit and is arranged within the port. The bushing is engaged with and laterally between the conduit and the boss. The bushing is configured from or otherwise includes a cellular material. The cellular material may be or otherwise include a cellular metal material and/or a cellular composite material.
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公开(公告)号：US12065985B2
公开(公告)日：2024-08-20
申请号：US18030151
申请日：2021-10-04
申请人： SAFRAN CERAMICS
发明人： Thierry Guy Xavier Tesson , Christophe Jean François Thorel , Christophe Paul Aupetit , Thierry Jacques Albert Le Docte , Philippe Avenel
CPC分类号： F02K1/04 , F01D25/30 , F02K1/805 , F02K1/827 , F05D2240/55 , F05D2260/96
摘要： The present invention relates to an assembly for a turbomachine turbine extending along an axis (X), comprising: —an ejection cone (100) comprising a radially outer annular wall (102) defining a flow duct for a flow of hot gases and a sound box radially arranged inside the outer annular wall (102), the sound box comprising a radially inner annular wall (104), —a connecting member (106) intended to be axially inserted between the exhaust housing and the ejection cone (100), the connecting member (106) comprising an upstream annular flange (108) intended to be attached to the exhaust housing and a plurality of downstream securing tabs (110) connected to the inner annular wall (104), —an annular sealing shroud (112) comprising an upstream portion surrounding the securing tabs (110) of the connecting member (106) so as to cover the spaces circumferentially located between the securing tabs (110) and axially located between the upstream annular flange (108) of the connecting member (106) and the radially inner annular wall (104).
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公开(公告)号：US12065969B2
公开(公告)日：2024-08-20
申请号：US17304352
申请日：2021-06-18
CPC分类号： F02C7/08 , F01D25/30 , F01N5/02 , F02C6/16 , F02C7/045 , F02C7/10 , F02C7/224 , F01D25/305 , F02C6/08 , F05D2240/126 , F05D2250/185 , F05D2260/213 , F05D2260/232 , F05D2260/96
摘要： Disclosed is an exhaust duct (1) for a gas turbine engine (50), comprising a silencer section (12). At least two plate-shaped silencer baffles (20) are provided inside the silencer section (12). At least one of the plate-shaped silencer baffles is configured as a heat exchange device in that it comprises at least one internal cavity (22) suitable for receiving a heat exchange fluid and leakproof with respect to the interior of the exhaust duct, wherein the at least one internal cavity is fluidly connected to the outside of the exhaust duct at an inlet port and an outlet port (23, 24). This device is useful for recuperating exhaust heat from exhaust gases of the gas turbine engine without the expense and additional space required for providing a heat recovery steam generator.
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公开(公告)号：US20240229741A1
公开(公告)日：2024-07-11
申请号：US18428254
申请日：2024-01-31
CPC分类号： F02K1/48 , F01D25/30 , F05D2220/323 , F05D2240/128 , F05D2260/96
摘要： An exhaust nozzle for a gas turbine engine. The exhaust nozzle comprises a nozzle body having an upstream end axially spaced from a downstream end with respect to an axial centerline of the nozzle body, and a plurality of chevrons circumferentially spaced apart and extending downstream from the downstream end. Each chevron includes an inner wall radially spaced from an outer wall, a root and a tip axially spaced from the root. At least one chevron of the plurality of chevrons includes a first segment extending axially downstream from the root, a second segment extending axially downstream from the first segment, and a third segment extending axially downstream from the second segment to the tip. The inner wall extends along the first segment, the second segment, and third the segment. The first segment is distinguishable from the second segment and the second segment is distinguishable from the third segment.
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公开(公告)号：US11933186B2
公开(公告)日：2024-03-19
申请号：US17731653
申请日：2022-04-28
CPC分类号： F01D25/06 , F01D5/16 , F01D25/30 , F05D2230/64 , F05D2240/12 , F05D2260/96
摘要： Vibrational damping assemblies, turbomachine airfoils, and exhaust diffusers are provided. A vibrational damping assembly includes at least one pin coupled to the turbomachine component. The at least one pin has a pin body and a disk coupled to the pin body. The vibrational damping assembly further includes at least one plate disposed between the disk and the turbomachine component. The at least one plate is movable between the disk and the turbomachine component relative to the plurality of pins and relative to the turbomachine component to dampen vibrations experienced by the turbomachine component.
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公开(公告)号：US11873726B2
公开(公告)日：2024-01-16
申请号：US18314976
申请日：2023-05-10
发明人： Ik Sang Lee , Willy Hofmann
CPC分类号： F01D25/28 , F01D9/02 , F01D9/041 , F01D25/30 , F05D2240/122
摘要： A strut provided in an exhaust diffuser and having an airfoil-shaped cross-section is provided. The strut may include a cut portion configured to be formed in a trailing edge in a span direction. The cut portion is configured to provide a stepped portion in at least a portion of the trailing edge.
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公开(公告)号：US11840937B2
公开(公告)日：2023-12-12
申请号：US17554816
申请日：2021-12-17
发明人： Russell Stratton
CPC分类号： F01D25/30 , F01N3/24 , F01N2470/02 , F01N2570/14 , F01N2590/00 , F05D2220/323 , F05D2260/609 , F05D2260/61 , F05D2270/082
摘要： A diffuser nozzle for a gas turbine engine includes a housing disposed about a nozzle axis and extending between a first nozzle end and a second nozzle end. The housing defines a nozzle duct. A plurality of walls is disposed within the nozzle duct. The plurality of walls subdivides the nozzle duct into a plurality of duct sections. The plurality of walls further defines a plurality of axially-extending duct segments of the nozzle duct such that within a first axially-extending duct segment, the duct cross-sectional area of a first duct section of the plurality of duct sections is greater than the duct cross-sectional area of each other duct section and within a second axially-extending duct segment, the duct cross-sectional area of a second duct section of the plurality of duct sections is greater than the duct cross-sectional area of each other duct section.
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公开(公告)号：US20230358339A1
公开(公告)日：2023-11-09
申请号：US18222133
申请日：2023-07-14
摘要： A pipe supporting structure includes: a plate-like member being into contact with an outside surface of a pipe; a tube-like member having a tubular shape and configured to support the plate-like member; and a base configured to support the tube-like member, wherein the plate-like member includes a supported portion supported by the tube-like member and an inner side portion surrounded by the supported portion, and the inner side portion has a smaller heat capacity per unit volume than the supported portion.
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公开(公告)号：US11692459B2
公开(公告)日：2023-07-04
申请号：US17655748
申请日：2022-03-21
发明人： Nicolas Pommier , Mathieu Bissardon , Mathieu Delalandre , Stephane Nicolas Piron , Olivier Renon
CPC分类号： F01D25/24 , F01D17/145 , F01D25/162 , F01D25/30 , F02C6/08 , F02C7/32 , F05D2220/30 , F05D2230/10 , F05D2230/232 , F05D2230/60 , Y02T50/60
摘要： A method for manufacturing a turbine engine part in which a first rough casting element includes a first face and a second face opposite to each other is assembled by the second face on an orifice which has a second element of the part. The method includes machining a through-cavity in the first element which opens at the first face and from the second face of the first element and machining the first face of the first element so as to form an area suitable for ensuring the attachment of a conduit on the first element. The machining of the cavity and of the first face is achieved by using a machining reference frame based on the second element.
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公开(公告)号：US11655730B2
公开(公告)日：2023-05-23
申请号：US16746962
申请日：2020-01-20
发明人： Ik Sang Lee , Willy Hofmann , Young Chan Yang
CPC分类号： F01D25/162 , F01D9/041 , F01D25/30 , F01D25/24 , F05D2240/12 , F05D2240/14
摘要： A strut structure of a gas turbine, an exhaust diffuser and a gas turbine including the same are provided. The strut structure of a gas turbine, the strut structure being formed in an annular exhaust passage formed between an inner casing and an outer casing of the gas turbine, includes a strut housing configured to include a lower end which is connected to the inner casing and an upper end which is connected to the outer casing, and a strut groove configured to be formed on at least one end of the upper end and the lower end of the strut housing to connect a front end and a rear end thereof.
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