专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明申请

US20190093560A1 MULTIPLE CIRCUIT MANIFOLDS 审中-公开
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.
发明人： Jason A. Ryon , Jacob Greenfield , Lev Alexander Prociw
IPC分类号： F02C7/22 , F23R3/36 , F23R3/34
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.

2. 发明申请

US20180335211A1 COMBUSTOR PANEL ENDRAIL INTERFACE 审中-公开
公开(公告)号：US20180335211A1
公开(公告)日：2018-11-22
申请号：US15599159
申请日：2017-05-18
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SAN QUACH , JEFFREY T. MORTON , MATTHEW D. PAREKH
IPC分类号： F23R3/00 , F23R3/06
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.

3. 发明申请

US20180274784A1 COMBUSTOR HEAT SHIELD SEALING 审中-公开
公开(公告)号：US20180274784A1
公开(公告)日：2018-09-27
申请号：US15995721
申请日：2018-06-01
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Daniel HAYEK , Jason HERBORTH , Yen-Wen WANG
IPC分类号： F23R3/00 , F23R3/60
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.

4. 发明申请

US20180266689A1 COMBUSTOR LINER WITH GASKET FOR GAS TURBINE ENGINE 审中-公开
公开(公告)号：US20180266689A1
公开(公告)日：2018-09-20
申请号：US15463168
申请日：2017-03-20
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Stephen K. Kramer , Jose E. Ruberte Sanchez
IPC分类号： F23R3/06 , F23R3/00 , F02C7/12 , F23R3/60
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.

5. 发明申请

US20180010801A1 PARTICULATE BUILDUP PREVENTION IN IGNITOR AND FUEL NOZZLE BOSSES 审中-公开
公开(公告)号：US20180010801A1
公开(公告)日：2018-01-11
申请号：US15205822
申请日：2016-07-08
申请人： PRATT & WHITNEY CANADA CORP.
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.

6. 发明授权

US09689573B2 Combustion equipment having a sealing member that includes a flexible sleeve 有权
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
发明人： Jason Robert Potts , Simon Mark Jolliff
IPC分类号： F23R3/28 , F02C7/28 , F02C7/22 , F23R3/00
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.

7. 发明授权

US09587831B2 Cooled combustor seal 有权
标题翻译：冷却燃烧器密封
公开(公告)号：US09587831B2
公开(公告)日：2017-03-07
申请号：US13686303
申请日：2012-11-27
申请人： United Technologies Corporation
发明人： Jonathan M. Jause , Kevin Joseph Low , David Kwoka
IPC分类号： F02C7/28 , F23R3/00 , F02C7/12 , F02C7/20 , F02C7/24 , F02C7/26 , F23R3/04
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。

8. 发明申请

US20170059160A1 COMBUSTOR ASSEMBLY FOR A TURBINE ENGINE 审中-公开
标题翻译：用于涡轮发动机的COMBUSTOR组件
公开(公告)号：US20170059160A1
公开(公告)日：2017-03-02
申请号：US14842883
申请日：2015-09-02
申请人： General Electric Company
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。

9. 发明授权

US09528383B2 System for sealing between combustors and turbine of gas turbine engine 有权
标题翻译：燃气轮机和燃气轮机之间的密封系统
公开(公告)号：US09528383B2
公开(公告)日：2016-12-27
申请号：US14145774
申请日：2013-12-31
申请人： General Electric Company
发明人： Keith Cletus Belsom
IPC分类号： F01D9/02 , F23R3/60 , F01D9/04 , F01D11/00
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。

10. 发明申请

US20160369701A1 TURBOMACHINE SPARKPLUG FIXING ASSEMBLY 有权
标题翻译：涡轮发动机固定装置
公开(公告)号：US20160369701A1
公开(公告)日：2016-12-22
申请号：US15106162
申请日：2014-11-26
申请人： Snecma
发明人： Pierre-Francois Simon Paul Pireyre , Francois Leglaye , David Gino Stifanic
IPC分类号： F02C7/266 , H01T13/08 , F02C3/14 , F23R3/00 , F23R3/28 , F23R3/10
CPC分类号： F02C7/266 , F02C3/14 , F05D2220/32 , F05D2240/35 , F23D2207/00 , F23D2209/00 , F23D2211/00 , F23R3/002 , F23R3/10 , F23R3/28 , F23R3/60 , F23R2900/00005 , F23R2900/00012 , H01T13/08
摘要： Assembly comprising, on a turbomachine:—a combustion chamber (30) having a longitudinal axis (30a) and comprising: internal and external longitudinal walls (90) having a first opening (90a) substantially transverse to said axis (30a), an outer casing (110) having a second opening (110a) likewise substantially transverse to said axis (30a),—a turbomachine sparkplug (150),—a device (130) for radially securing the sparkplug (150), which device (130) comprises a sparkplug adapter (160) fixed toward a first end to the outer casing (110), facing the second opening (110a) and through which adapter and casing the sparkplug (150) in question passes, and a sparkplug guide (190) kept in contact with the external longitudinal wall (90), facing the first opening (90a) and through which the sparkplug (150) passes to emerge in the combustion chamber (30), the sparkplug (150) and the sparkplug guide (190) each having a screw thread (103, 105), the screw threads (103, 105) being screwed together so as to stabilize the sparkplug (150) radially to the axis (30a) of the combustion chamber (30) with respect to said external longitudinal wall (90), and—in this condition, the sparkplug (150) and the sparkplug guide (190) are mounted freely with respect to the outer casing (110) in a direction substantially radial to the axis of the second opening (110a).
摘要翻译：在涡轮机上包括： - 具有纵向轴线（30a）的燃烧室（30），并且包括：具有基本上横向于所述轴线（30a）的第一开口（90a）的内部和外部纵向壁（90）壳体（110）具有同样基本上横向于所述轴线（30a）的第二开口（110a）， - 涡轮机火花塞（150）， - 用于径向固定所述火花塞（150）的装置（130），所述装置面向第二开口（110a）的朝向第一端固定到外壳（110）的火花塞适配器（160）以及通过其中的火花塞（150）的适配器和壳体通过的火花塞引导件（190）保持在与外部纵向壁（90）接触，面向第一开口（90a）并且火花塞（150）通过其在燃烧室（30）中出现，火花塞（150）和火花塞引导件（190）各自具有一个螺纹（103,105），螺纹（103,105）被拧在一起以便相对于所述外部纵向壁（90）将所述火花塞（150）径向地稳定到所述燃烧室（30）的轴线（30a），并且在该状态下，所述火花塞（150）和所述火花塞引导件 190）相对于外壳（110）沿与第二开口（110a）的轴线基本上径向的方向自由地安装。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式