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公开(公告)号：US11668463B2
公开(公告)日：2023-06-06
申请号：US17392884
申请日：2021-08-03
发明人： Tin-Cheung John Hu
CPC分类号： F23R3/06 , F23R3/002 , F02C7/18 , F05D2260/202 , F23M5/085 , F23R2900/00012 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044
摘要： A combustor of an aircraft engine comprises a liner defining a primary and a dilution zone having a hot surface exposed to a flow of combustion gases traveling from the primary zone downstream to the dilution zone and a cold surface. Dilution holes extending through the liner from the cold to the hot surface delimit the primary from the dilution zone. Effusion holes extending through the liner from the cold to the hot surface direct cooling air into the dilution zone. Two or more rows of effusion holes positioned within three dilution hole diameters downstream of the dilution holes are oriented relative to the liner to direct the cooling air in a cooling direction that is at least one of normal to the direction of the flow of gases passing adjacent the effusion holes, and against the direction of the flow of gases passing adjacent the effusion holes.
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公开(公告)号：US20190093560A1
公开(公告)日：2019-03-28
申请号：US15714265
申请日：2017-09-25
申请人： Delavan Inc.
CPC分类号： F02C7/222 , F05D2220/32 , F05D2240/35 , F23R3/10 , F23R3/346 , F23R3/36 , F23R2900/00012
摘要： A fluid manifold includes a manifold body, a first annular passage and a second annular passage. The first annular passage is defined within the manifold body between a first passage inlet and a first passage outlet downstream from the first passage inlet. The second annular passage is defined within the manifold body nested radially outward from the first annular passage, and between a second passage inlet and a second passage outlet downstream from the second passage inlet. The first and second annular passages are concentric about a manifold axis. The first passage outlet and the second passage outlet are positioned at the same axial position relative to the manifold axis.
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公开(公告)号：US20180335211A1
公开(公告)日：2018-11-22
申请号：US15599159
申请日：2017-05-18
发明人： SAN QUACH , JEFFREY T. MORTON , MATTHEW D. PAREKH
CPC分类号： F23R3/002 , F23R3/06 , F23R2900/00012 , F23R2900/00017 , F23R2900/03041 , F23R2900/03044
摘要： A combustor of a gas turbine engine may include a combustor shell, a first combustor panel coupled to the combustor shell, and a second combustor panel coupled to the combustor shell. The first combustor panel may have a first endrail and the second combustor panel may have a second endrail. An annular cooling cavity may be defined between the combustor shell and the first and second combustor panels and a channel may be defined between the first endrail and the second endrail, wherein direct line-of-sight through the channel from the annular cooling cavity to a combustor chamber is obstructed. Said differently, the interface between the adjacent endrails may be non-linear, in a direction from the annular cooling cavity to the combustor chamber.
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公开(公告)号：US20180274784A1
公开(公告)日：2018-09-27
申请号：US15995721
申请日：2018-06-01
发明人： Daniel HAYEK , Jason HERBORTH , Yen-Wen WANG
CPC分类号： F23R3/002 , F23R3/60 , F23R2900/00012
摘要： A method and an apparatus for reducing airflow leakage between a combustor liner and a rail of a heat shield mounted to an inner surface of the combustor liner. The method comprises locally deforming the combustor liner in sealing engagement with the rail by applying a pressure on the outer surface of the combustor liner over the rail of the heat shield. A tool, such as a sealing clip, may be mounted in pressing engagement with the outer surface of the combustor liner to apply forces locally on the liner over the rail of the heat shield.
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公开(公告)号：US20180266689A1
公开(公告)日：2018-09-20
申请号：US15463168
申请日：2017-03-20
CPC分类号： F23R3/06 , F02C7/12 , F05D2260/201 , F05D2260/202 , F23R3/002 , F23R3/50 , F23R3/60 , F23R2900/00012 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044 , Y02T50/675
摘要： A gasket for installation within a cavity between a support shell and a liner panel of a combustor wall assembly, the support shell having a multiple of impingement holes, and the liner panel having a multiple of film holes, the gasket including a multiple of cells arranged with respect to the multiple of impingement holes and the multiple of film holes, wherein at least one of the multiple of cells segregate a respective subset of the multiple of impingement holes and a subset of the multiple of film holes.
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公开(公告)号：US20180010801A1
公开(公告)日：2018-01-11
申请号：US15205822
申请日：2016-07-08
发明人： Jakub Strzepek , Sri Sreekanth , Kian McCaldon , Honza Stastny , Dan Titrica
IPC分类号： F23R3/60
CPC分类号： F23R3/60 , F02C7/264 , F05D2260/607 , F23R3/283 , F23R2900/00012
摘要： A floating collar assembly for a gas turbine engine combustor includes a ferrule having a peripheral wall and a recessed surface bounded by the peripheral wall, the recessed surface of the ferrule including a particulate collecting groove adjacent the peripheral wall, and a cap secured to the peripheral wall of the ferrule. The recessed surface of the ferrule, an interior surface of the cap and the peripheral wall of the ferrule define a cavity. A floating collar is disposed within the cavity and includes a peripheral flange inwardly spaced a distance from the peripheral wall of the ferrule.
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公开(公告)号：US09689573B2
公开(公告)日：2017-06-27
申请号：US14303223
申请日：2014-06-12
申请人： ROLLS-ROYCE PLC
CPC分类号： F23R3/283 , F02C7/222 , F02C7/28 , F23R3/002 , F23R2900/00001 , F23R2900/00012 , Y02T50/671 , Y10T29/49233
摘要： Combustion equipment for use in a gas turbine engine is provided. The combustion equipment includes an inner and outer case, wherein the outer case encloses the inner case creating a cavity located between the two cases. The combustion equipment also has a fuel delivery device for delivering fuel into a combustion region within the inner case, wherein the fuel delivery device passes through a hole in the outer case and a corresponding hole in the inner case. The combustion equipment also includes a seal assembly to prevent the leaking of pressurized gas into the cavity located between the outer and inner cases via the hole through which fuel delivery device passes. The seal assembly includes a flexible sleeve that extends around the fuel delivery device and interconnects the inner case with the outer case, permitting relative movement of the inner and outer cases when the combustion equipment is in use.
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公开(公告)号：US09587831B2
公开(公告)日：2017-03-07
申请号：US13686303
申请日：2012-11-27
发明人： Jonathan M. Jause , Kevin Joseph Low , David Kwoka
CPC分类号： F23R3/002 , F02C7/12 , F02C7/20 , F02C7/24 , F02C7/26 , F02C7/28 , F23R3/04 , F23R2900/00012
摘要： A cooled combustor seal having a plurality of channels enabling cooling air to pass from outside of a combustion chamber to cool an area inside the combustion chamber around the seal is disclosed. The channels may be provided through a slider, a housing, and/or a washer of the combustor seal. One set of channels or multiple of sets of channels may be provided in the combustor seal. Each of these sets of channels may be in the slider, housing, or washer. The cooled combustor seal may be used in conjunction with an igniter to purge a cavity between the seal and the igniter.
摘要翻译： 公开了一种冷却的燃烧器密封件，其具有多个通道，使得冷却空气能够从燃烧室的外部通过以冷却密封件周围的燃烧室内的区域。 通道可以通过燃烧器密封件的滑块，壳体和/或垫圈来提供。 可以在燃烧器密封件中设置一组通道或多组通道。 这些通道组中的每一个可以在滑块，壳体或垫圈中。 冷却的燃烧器密封件可以与点火器一起使用以清除密封件和点火器之间的空腔。
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公开(公告)号：US20170059160A1
公开(公告)日：2017-03-02
申请号：US14842883
申请日：2015-09-02
发明人： Nicholas John Bloom , Daniel Kirtley , Michael Alan Stieg , Brian Christopher Towle , Chad Holden Sutton
IPC分类号： F23R3/00
CPC分类号： F23R3/007 , F23R3/50 , F23R3/60 , F23R2900/00012
摘要： A combustor assembly for a gas turbine engine is provided. The combustor assembly includes a liner at least partially defining a combustion chamber and extending between an aft end a forward end generally along an axial direction. The combustor assembly also includes an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner. A cap is positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome. The cap includes a surface configured to contact at least one of the enclosed surface of the annular dome and the forward end of the liner. Such a configuration may form a substantially airtight seal between the forward end of the liner and the annular dome despite a relative thermal expansion between the components.
摘要翻译： 提供了一种用于燃气涡轮发动机的燃烧器组件。 燃烧器组件包括至少部分地限定燃烧室并且在后端大致沿轴向方向的前端之间延伸的衬套。 燃烧器组件还包括环形圆顶，其包括限定用于接收衬套的前端的槽的封闭表面。 盖子定位在衬套的前端并且至少部分地定位在由环形圆顶的封闭表面限定的槽内。 盖包括被配置为接触环形圆顶的封闭表面和衬垫的前端中的至少一个的表面。 这种构造可以在衬套的前端和环形圆顶之间形成基本上气密的密封，尽管组件之间相对热膨胀。
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10.发明授权公开(公告)号：US09528383B2
公开(公告)日：2016-12-27
申请号：US14145774
申请日：2013-12-31
发明人： Keith Cletus Belsom
CPC分类号： F02C7/28 , F01D9/023 , F01D9/041 , F01D11/003 , F02C3/14 , F05D2220/3212 , F05D2240/55 , F23R3/46 , F23R3/60 , F23R2900/00012
摘要： A gas turbine engine includes a gas turbine and a plurality of combustors each in fluid communication with the gas turbine. The gas turbine engine includes a first seal disposed between the gas turbine and the plurality of turbine combustors. The first seal is configured to sealingly engage with the gas turbine and at least two of the plurality of turbine combustors. The gas turbine engine also includes a second seal disposed between the gas turbine and the plurality of turbine combustors. The second seal is configured to sealingly engage with the gas turbine and at least two of the plurality of turbine combustors.
摘要翻译： 燃气涡轮发动机包括燃气轮机和多个与燃气轮机流体连通的燃烧器。 燃气涡轮发动机包括设置在燃气轮机和多个涡轮燃烧器之间的第一密封件。 第一密封件构造成与燃气轮机和多个涡轮燃烧器中的至少两个密封地接合。 燃气涡轮发动机还包括设置在燃气轮机和多个涡轮燃烧器之间的第二密封件。 第二密封件构造成与燃气轮机和多个涡轮机燃烧器中的至少两个密封地接合。
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