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. 发明授权

US10648346B2 Shroud configurations for turbine rotor blades 有权
公开(公告)号：US10648346B2
公开(公告)日：2020-05-12
申请号：US15203027
申请日：2016-07-06
申请人： General Electric Company
发明人： Xiuzhang James Zhang , Kevin Richard Kirtley , Lisa DeBellis
IPC分类号： F01D5/20 , F01D5/22 , F01D11/08
摘要： A turbine rotor blade that includes a tip shroud attached to the outboard tip of the airfoil. The tip shroud may include an axially and circumferentially extending planar component in which an inboard surface opposes an outboard surface, and a shroud edge that connects the inboard surface to the outboard surface and defines an outboard profile of the tip shroud. The tip shroud may include a seal rail protruding from the outboard surface of the tip shroud and a cutter tooth disposed on the seal rail. The cutter tooth may be formed as a circumferential section of the seal rail that is axially thickened. The seal rail may further include a leakage gap formed therethrough that is configured to increase a leakage level during operation.

2. 发明申请

US20180355727A1 Turbomachine Blade Cooling Structure and Related Methods 审中-公开
公开(公告)号：US20180355727A1
公开(公告)日：2018-12-13
申请号：US15620896
申请日：2017-06-13
申请人： General Electric Company
发明人： Jalindar Appa Walunj , Shashwat Swami Jaiswal , Stephen Paul Wassynger , Xiuzhang James Zhang
IPC分类号： F01D5/08 , F01D5/22
摘要： A blade for a turbomachine includes an airfoil extending radially between a root and a tip with a tip shroud coupled to the tip of the airfoil. The tip shroud includes a platform having an outer surface extending generally perpendicular to the airfoil. The tip shroud also includes a forward rail extending radially outward from the outer surface of the platform. The forward rail is oriented generally perpendicular to a hot gas path of the turbomachine. A cooling cavity is defined in a central portion of the platform. The tip shroud also includes a cooling channel extending between the cooling cavity and an ejection slot formed in the forward rail. The ejection slot is positioned radially outward of the outer surface of the platform of the tip shroud.

3. 发明授权

US09464536B2 Sealing arrangement for a turbine system and method of sealing between two turbine components 有权
标题翻译：涡轮机系统的密封装置和两个涡轮机部件之间的密封方法
公开(公告)号：US09464536B2
公开(公告)日：2016-10-11
申请号：US13654822
申请日：2012-10-18
申请人： General Electric Company
发明人： Xiuzhang James Zhang , Gary Michael Itzel , Ibrahim Sezer
IPC分类号： F01D11/12 , F01D11/00
CPC分类号： F01D11/006 , F01D11/122
摘要： A sealing arrangement for a turbine system includes a bucket having an outer tip and at least one bucket ridge extending radially outwardly from the outer tip, the at least one bucket ridge comprising an abradable material. Also included is a stationary shroud disposed radially outwardly from the outer tip of the bucket. Further included is at least one shroud ridge extending radially inwardly from the stationary shroud toward the outer tip of the bucket, the at least one shroud ridge comprising the abradable material.
摘要翻译：涡轮机系统的密封装置包括具有外部尖端的桶，以及从外部末端径向向外延伸的至少一个铲斗脊，所述至少一个铲斗脊包含可磨损材料。还包括从桶的外端径向向外设置的固定护罩。还包括至少一个护罩脊，其从固定护罩朝向桶的外部末端径向向内延伸，所述至少一个护罩脊包括可磨损材料。

4. 发明申请

US20150064010A1 Turbine Bucket Tip Shroud 有权
标题翻译：涡轮铲斗头罩
公开(公告)号：US20150064010A1
公开(公告)日：2015-03-05
申请号：US14011784
申请日：2013-08-28
申请人： General Electric Company
发明人： Xiuzhang James Zhang , Melbourne James Myers , Robert Joseph Testa, Jr. , Haiping Wang
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F01D5/225 , F05D2240/307 , F05D2240/81 , F05D2260/20 , F05D2260/201 , F05D2260/202
摘要： The present application provides a turbine bucket. The turbine bucket may include an airfoil and a tip shroud attached to the airfoil. The tip shroud may include a cooling core and an enhanced cooling surface.
摘要翻译：本申请提供了一种涡轮机桶。涡轮机桶可以包括附接到翼型件的翼型件和顶端罩。尖端护罩可以包括冷却芯和增强的冷却表面。

5. 发明授权

US10487660B2 Additively manufactured blade extension with internal features 有权
公开(公告)号：US10487660B2
公开(公告)日：2019-11-26
申请号：US15383228
申请日：2016-12-19
申请人： General Electric Company
发明人： Benjamin Paul Lacy , Kassy Moy Hart , Xiuzhang James Zhang
IPC分类号： F01D5/00 , F01D5/02 , F01D5/18 , F01D5/30 , B22F3/105 , B22F5/04 , F01D5/14
CPC分类号： F01D5/005 , B22F3/105 , B22F5/04 , F01D5/025 , F01D5/147 , F01D5/18 , F01D5/30 , F05D2220/30 , F05D2230/30 , F05D2230/80 , F05D2240/301 , F05D2240/60 , F05D2240/80 , Y02T50/671 , Y02T50/676
摘要： This disclosure provides components and methods for blade extensions with internal features. An airfoil extends from a root connector and includes an airfoil body defining at least one air channel enclosed within the airfoil body. The air channel extends to a build surface. An additive extension extends from the build surface of the airfoil body. The additive extension includes an additive structure extending the air channel from the build surface to an external surface of the additive extension.

6. 发明授权

US09995146B2 Turbine airfoil turbulator arrangement 有权
公开(公告)号：US09995146B2
公开(公告)日：2018-06-12
申请号：US14699607
申请日：2015-04-29
申请人： General Electric Company
发明人： Adebukola Oluwaseun Benson , Nicholas Alvin Hogberg , Gary Michael Itzel , Mitchell Allan Merrill , Xiuzhang James Zhang
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/187 , F05D2240/127 , F05D2260/2212 , F05D2260/22141
摘要： A turbine airfoil includes a leading edge and a trailing edge. Also included is a cooling channel extending in a radial direction and tapering inwardly toward the trailing edge, the cooling channel at least partially defined by a pressure side face and a suction side face. Further included is a first plurality of turbulators protruding from one of the pressure side face and the suction side face to define a first height, the first plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other. Yet further included is a second plurality of turbulators protruding from one of the pressure side face and the suction side face to define a second height that is less than the first height, the second plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other.

7. 发明授权

US09759070B2 Turbine bucket tip shroud 有权
公开(公告)号：US09759070B2
公开(公告)日：2017-09-12
申请号：US14011784
申请日：2013-08-28
申请人： General Electric Company
发明人： Xiuzhang James Zhang , Melbourne James Myers , Robert Joseph Testa, Jr. , Haiping Wang
IPC分类号： F01D5/18 , F01D5/22
CPC分类号： F01D5/187 , F01D5/186 , F01D5/225 , F05D2240/307 , F05D2240/81 , F05D2260/20 , F05D2260/201 , F05D2260/202
摘要： The present application provides a turbine bucket. The turbine bucket may include an airfoil and a tip shroud attached to the airfoil. The tip shroud may include a cooling core and an enhanced cooling surface.

8. 发明授权

US09527262B2 Layered arrangement, hot-gas path component, and process of producing a layered arrangement 有权
标题翻译：层叠布置，热气路径部件，以及分层布置的制造工序
公开(公告)号：US09527262B2
公开(公告)日：2016-12-27
申请号：US13630708
申请日：2012-09-28
申请人： GENERAL ELECTRIC COMPANY
发明人： Xiuzhang James Zhang , Haiping Wang
IPC分类号： C04B37/00 , F04D29/44 , F03D1/04 , B32B3/26 , B32B3/12 , F01D5/18 , F01D11/24 , C04B37/02 , B32B9/00 , B32B9/04 , B32B3/30 , B32B15/04 , B32B37/00 , F01D9/02 , B32B37/12 , B32B37/14 , B32B37/16 , C04B37/04 , C04B35/117 , C04B35/48 , C04B35/185 , C04B35/01 , C04B35/515 , C04B35/584
CPC分类号： B32B3/263 , B32B3/12 , B32B3/26 , B32B3/30 , B32B9/005 , B32B9/04 , B32B15/04 , B32B37/0084 , B32B37/12 , B32B37/144 , B32B37/146 , B32B37/16 , B32B2250/03 , B32B2262/105 , B32B2262/106 , B32B2307/304 , B32B2311/00 , B32B2315/02 , B32B2603/00 , B32B2605/18 , C04B35/01 , C04B35/117 , C04B35/185 , C04B35/48 , C04B35/5156 , C04B35/584 , C04B37/003 , C04B37/025 , C04B37/04 , C04B2237/068 , C04B2237/34 , C04B2237/341 , C04B2237/343 , C04B2237/36 , C04B2237/363 , C04B2237/365 , C04B2237/368 , C04B2237/38 , C04B2237/403 , C04B2237/405 , C04B2237/406 , C04B2237/597 , C04B2237/704 , C04B2237/706 , C04B2237/72 , F01D5/187 , F01D9/02 , F01D11/24 , F05D2240/11 , F05D2240/12 , F05D2240/126 , F05D2240/15 , F05D2240/24 , F05D2240/303 , F05D2240/81 , F05D2250/232 , F05D2250/241 , F05D2250/28 , F05D2250/291 , F05D2260/20 , F05D2260/204 , F05D2260/22141 , F05D2300/175 , F05D2300/20 , F05D2300/6033 , Y10T428/24562 , Y10T428/24612 , Y10T428/24942 , Y10T428/24967
摘要： A layered arrangement, a hot-gas path component, and a process of producing a layered arrangement are disclosed. The layered arrangement includes a substrate layer, a ceramic matrix composite layer, and a non-metal spacer between the substrate layer and the ceramic matrix composite layer configured to define one or more pockets. The hot-gas-path component includes a nickel-based superalloy layer, a ceramic matrix composite layer, and a ceramic spacer between the nickel-based superalloy layer and the ceramic matrix composite layer. The ceramic spacer is mechanically secured to one or both of the substrate layer and the ceramic matrix composite layer, and the ceramic spacer is bonded to the substrate layer or the ceramic matrix composite layer. The process includes securing a non-metal spacer between a substrate layer and a ceramic matrix composite layer of the layered arrangement.
摘要翻译：公开了一种分层布置，热气路径部件和制造分层布置的工艺。分层布置包括基底层，陶瓷基质复合层和在衬底层和陶瓷基质复合层之间的非金属间隔物，其被配置为限定一个或多个口袋。热气路部件包括镍基超合金层，陶瓷基复合层和镍基超合金层与陶瓷基复合层之间的陶瓷间隔物。将陶瓷间隔件机械地固定到基底层和陶瓷基复合层中的一个或两个，陶瓷间隔物结合到基底层或陶瓷基复合层。该方法包括在分层布置的基底层和陶瓷基体复合层之间固定非金属间隔物。

9. 发明申请

US20160319673A1 ROTOR BLADE HAVING A FLARED TIP 审中-公开
标题翻译：带有刀尖的转子叶片
公开(公告)号：US20160319673A1
公开(公告)日：2016-11-03
申请号：US14699321
申请日：2015-04-29
申请人： General Electric Company
发明人： Jeffrey Clarence Jones , Xiuzhang James Zhang , Mitchell Allan Merrill
IPC分类号： F01D5/18 , F02C7/18 , F02C3/04
CPC分类号： F01D5/187 , F01D5/20 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2240/304 , F05D2240/307 , F05D2240/35 , F05D2250/294 , F05D2250/324 , F05D2260/202
摘要： A rotor blade includes an airfoil having a blade tip and a tip cavity formed at the blade tip. The tip cavity includes a tip cap that is recessed radially inwardly from the tip and surrounded continuously by pressure and suction side walls of the airfoil. The tip cap further includes an aperture that extends through the tip cap and provides for fluid communication between an internal cavity defined within the airfoil and the tip cavity. An exhaust port provides for fluid communication out the tip cavity through one of the pressure side wall, the suction side wall or the trailing edge. A portion of at least one of the suction side wall and the pressure side wall that defines the tip cavity extends obliquely outwardly from the tip cavity with respect to a radial direction.
摘要翻译：转子叶片包括具有形成在叶片尖端处的叶片尖端和尖端腔的翼型件。尖端腔包括从尖端径向向内凹入并且被翼型的压力和吸力侧壁连续围绕的顶盖。尖端帽还包括一个孔，其延伸穿过顶端帽，并提供在翼型内限定的内腔与尖端腔之间的流体连通。排气口提供通过压力侧壁，吸力侧壁或后缘中的一个流体连通出口腔。限定尖端腔的吸入侧壁和压力侧壁中的至少一个的一部分相对于径向方向从尖端腔倾斜向外延伸。

10. 发明申请

US20160319672A1 ROTOR BLADE HAVING A FLARED TIP 审中-公开
标题翻译：带有刀尖的转子叶片
公开(公告)号：US20160319672A1
公开(公告)日：2016-11-03
申请号：US14699308
申请日：2015-04-29
申请人： General Electric Company
发明人： Jeffrey Clarence Jones , Xiuzhang James Zhang
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F05D2250/314 , F05D2250/324 , F05D2250/713
摘要： A rotor blade includes an airfoil having a blade tip and a tip cavity formed at the blade tip. The blade tip defines a radially outer surface of the airfoil. The tip cavity includes a tip cap that is recessed radially inwardly from the tip and surrounded by pressure and suction side walls of the airfoil. The tip cap is in fluid communication with an internal cavity defined within the airfoil. A portion of at least one of the suction side wall or the pressure side wall that defines the tip cavity extends obliquely outwardly from the tip cavity. A plurality of slots is defined in at least one of the suction side wall or the pressure side wall along the radially outer surface proximate to the trailing edge of the airfoil.
摘要翻译：转子叶片包括具有形成在叶片尖端处的叶片尖端和尖端腔的翼型件。叶片尖端限定翼型件的径向外表面。尖端腔包括从尖端径向向内凹入并被翼型的压力和吸力侧壁包围的顶盖。顶盖与限定在翼型内的内部空腔流体连通。限定尖端腔的吸入侧壁或压力侧壁中的至少一个的一部分从尖端腔倾斜向外延伸。吸入侧壁或压力侧壁中的至少一个沿着靠近翼型的后缘的径向外表面限定多个狭槽。

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