专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

31. 发明授权

US09605544B2 Aerofoil 有权
公开(公告)号：US09605544B2
公开(公告)日：2017-03-28
申请号：US14333033
申请日：2014-07-16
申请人： ROLLS-ROYCE PLC
发明人： Ian Tibbott , Dougal Richard Jackson
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/18 , F01D5/187 , F05D2260/201 , F05D2260/202 , F05D2260/22141
摘要： An aerofoil component of a gas turbine engine has an aerofoil portion which spans, in use, a working gas annulus of the engine. The aerofoil portion has a pressure side outer wall and a suction side outer wall, each extending from the leading edge to the trailing edge of the aerofoil portion. The aerofoil portion further has one or more main passages which extend in the annulus-spanning direction of the aerofoil portion and which receive, in use, a flow of coolant. The aerofoil portion further has one or more suction wall passages which extend in the annulus-spanning direction of the aerofoil portion and which receive, in use, a flow of coolant, each suction wall passage being bounded on opposing first sides by the suction side outer wall and an inner wall of the aerofoil portion, the inner wall separating the suction wall passages from the main passages.

32. 发明申请

US20170051624A1 BLADE OUTER AIR SEAL FIN COOLING ASSEMBLY AND METHOD 审中-公开
标题翻译：叶片外部密封件冷却组件和方法
公开(公告)号：US20170051624A1
公开(公告)日：2017-02-23
申请号：US15118521
申请日：2015-02-12
申请人： United Technologies Corporation
发明人： Dmitriy A. Romanov , Jose R. Paulino , Ken F. Blaney
IPC分类号： F01D11/08
CPC分类号： F01D11/08 , B22C9/10 , B22C9/24 , F01D11/24 , F05D2230/211 , F05D2240/11 , F05D2260/204 , F05D2260/22141 , F05D2300/13 , Y02T50/676
摘要： A blade outer air seal according to an exemplary aspect of the present disclosure includes, among other things, a body to be distributed circumferentially about a blade array. The body has a plurality of grooves, which can, for example, improve the aerodynamic efficiency of a turbine. A fin is between a first groove and a second groove of the plurality of grooves. The fin extends radially from the body and terminates at a radially inner fin face that provides one or more cooling outlets.
摘要翻译：根据本公开的示例性方面的叶片外部空气密封件尤其包括围绕叶片阵列周向分布的主体。主体具有多个凹槽，其可以例如改善涡轮机的空气动力学效率。翅片在多个凹槽的第一凹槽和第二凹槽之间。翅片从主体径向延伸并且终止于提供一个或多个冷却出口的径向内部翅片面。

33. 发明授权

US09574449B2 Internally coolable component for a gas turbine with at least one cooling duct 有权
标题翻译：具有至少一个冷却管道的燃气轮机的内部可冷却部件
公开(公告)号：US09574449B2
公开(公告)日：2017-02-21
申请号：US14237871
申请日：2012-08-02
申请人： Marcel Eifel , Daniel Gloss , Andreas Heselhaus , Stephan Klumpp , Marco Link , Uwe Sieber , Stefan Volker , Michael Wagner
发明人： Marcel Eifel , Daniel Gloss , Andreas Heselhaus , Stephan Klumpp , Marco Link , Uwe Sieber , Stefan Volker , Michael Wagner
IPC分类号： F01D5/18 , F02C7/12
CPC分类号： F01D5/187 , F02C7/12 , F05D2260/22141
摘要： An internally coolable component for a gas turbine with at least one cooling duct, on the inner surface of which swirl elements are arranged in the form of turbulators which extend transversely with respect to the main flow direction of a coolant is provided. In order to reduce pressure losses for the coolant in the cooling duct, pins with different heights are set up between the turbulators.
摘要翻译：提供了一种用于具有至少一个冷却管道的燃气轮机的内部可冷却部件，其内表面上设置有相对于冷却剂的主流动方向横向延伸的涡流体形式的涡流元件。为了减少冷却管道中的冷却剂的压力损失，在湍流器之间建立具有不同高度的销。

34. 发明申请

US20170022823A1 TURBINE ROTORS INCLUDING TURBINE BLADES HAVING TURBULATOR-COOLED TIP POCKETS 审中-公开
标题翻译：涡轮转子，包括具有涡轮机冷却提示口的涡轮叶片
公开(公告)号：US20170022823A1
公开(公告)日：2017-01-26
申请号：US14807683
申请日：2015-07-23
申请人： United Technologies Corporation
发明人： EDWARD F. PIETRASZKIEWICZ , BRANDON W. SPANGLER
IPC分类号： F01D5/20 , F01D5/02 , F01D5/18
CPC分类号： F01D5/20 , F01D5/02 , F01D5/18 , F05D2220/32 , F05D2240/307 , F05D2260/2212 , F05D2260/22141
摘要： A turbine blade is provided. The turbine blade includes a suction side wall including a first tip edge, a pressure side wall opposite the suction side wall and including a second tip edge. A tip wall extends between the suction side wall and the pressure side wall. The tip wall is recessed from the first tip edge and the second tip edge to define a tip pocket having a suction side wall tip section and a pressure side wall tip section. At least one turbulator is formed in the tip pocket on at least one of the following: the tip wall, the suction side wall tip section, and the pressure side wall tip section. The at least one turbulator formed on the tip wall is selectively positioned.
摘要翻译：提供涡轮叶片。涡轮叶片包括吸入侧壁，该吸力侧壁包括第一末端边缘，与吸力侧壁相对的压力侧壁，并且包括第二末端边缘。顶壁在吸力侧壁和压力侧壁之间延伸。尖端壁从第一末端边缘和第二末端边缘凹入，以限定具有吸力侧壁顶端部分和压力侧壁顶端部分的尖端口袋。至少一个湍流器在尖端口袋中形成在以下至少一个中：尖端壁，吸力侧壁顶端部分和压力侧壁顶端部分。形成在尖端壁上的至少一个湍流器被选择性地定位。

35. 发明授权

US09518468B2 Cooled component for the turbine of a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的涡轮机的冷却部件
公开(公告)号：US09518468B2
公开(公告)日：2016-12-13
申请号：US13359180
申请日：2012-01-26
申请人： Ian Tibbott , Dougal R. Jackson
发明人： Ian Tibbott , Dougal R. Jackson
IPC分类号： F01D5/18 , F01D9/06 , F01D5/20
CPC分类号： F01D5/18 , F01D5/186 , F01D5/187 , F01D5/188 , F01D5/20 , F01D9/06 , F01D9/065 , F05D2240/127 , F05D2240/81 , F05D2260/2212 , F05D2260/22141
摘要： A component for the turbine of a gas turbine engine is provided. The component two facing walls interconnected by one or more generally elongate divider members to partially define side-by-side, generally elongate, cooling fluid passage portions which form a multi-pass cooling passage within the component. The passage portions are connected in series fluid flow relationship by respective bends formed by joined ends of neighbouring of the passage portions. The component further includes one or more core tie linking passages formed in the divider members. One or more differential pressure reducing arrangements are formed in the multi-pass cooling passage adjacent respective of the core tie linking passages.
摘要翻译：提供了一种用于燃气涡轮发动机的涡轮机的部件。由两个面向对面的部件组成的壁由一个或多个大致细长的分隔件相互连接，以部分地限定并排大致细长的冷却流体通道部分，该部分形成多个部件内的多通道冷却通道。通道部分通过由相邻通道部分的连接端形成的相应的弯曲部以串联的流体流动关系连接。该部件还包括形成在分隔件中的一个或多个芯连接连接通道。在多通道冷却通道中形成有一个或多个差压减压装置，该多通道冷却通道与相互连接的芯连接通道相邻。

36. 发明授权

US09500099B2 Cover plate for a component of a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的部件的盖板
公开(公告)号：US09500099B2
公开(公告)日：2016-11-22
申请号：US13539806
申请日：2012-07-02
申请人： Brandon W. Spangler , Russell J. Bergman
发明人： Brandon W. Spangler , Russell J. Bergman
IPC分类号： F01D25/12 , F01D5/18
CPC分类号： F01D5/18 , F01D5/187 , F01D9/02 , F01D25/12 , F02C3/04 , F04D29/324 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2240/35 , F05D2240/81 , F05D2250/11 , F05D2260/201 , F05D2260/22141
摘要： A component for a gas turbine engine according to an exemplary embodiment of the present disclosure includes, among other possible things, a platform having a non-gas path side and a gas path side, an airfoil extending from the gas path side of the platform, and a cover plate positioned adjacent to the non-gas path side of the platform. The cover plate can include a first plurality of openings that communicate a first portion of a cooling air to a first cooling cavity of the platform and a second plurality of openings that can communicate a second portion of the cooling air to the second cooling cavity that is separate from the first cooling cavity. Each of the first cooling cavity and the second cooling cavity can include a plurality of augmentation features.
摘要翻译：根据本公开的示例性实施例的用于燃气涡轮发动机的部件除了其它可能的内容之外还包括具有非气体通路侧和气体通路侧的平台，从平台的气体路径侧延伸的翼型，以及邻近所述平台的非气体路径侧定位的盖板。盖板可以包括将冷却空气的第一部分连通到平台的第一冷却腔的第一多个开口以及可将冷却空气的第二部分连通到第二冷却腔的第二多个开口，与第一个冷却腔分开。第一冷却腔和第二冷却腔中的每一个可以包括多个增强特征。

37. 发明申请

US20160319698A1 BLADE OUTER AIR SEAL COOLING PASSAGE 审中-公开
标题翻译：叶片外密封冷却通道
公开(公告)号：US20160319698A1
公开(公告)日：2016-11-03
申请号：US15104092
申请日：2014-12-10
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Dmitriy A. Romanov
IPC分类号： F01D25/12 , F01D11/08
CPC分类号： F01D25/12 , F01D11/08 , F05D2220/32 , F05D2240/11 , F05D2260/201 , F05D2260/2212 , F05D2260/22141
摘要： A gas turbine engine component includes a structure including a first wall and a second wall that provide a cooling passage. The cooling passage extends a length from a first end to a second end. A cluster of impingement inlet holes is provided in the second wall at the first end. An outlet is provided at the second end.
摘要翻译：燃气涡轮发动机部件包括包括提供冷却通道的第一壁和第二壁的结构。冷却通道从第一端延伸到第二端。冲击入口孔的一组在第一端设置在第二壁上。在第二端设有出口。

38. 发明申请

US20160319671A1 TURBINE AIRFOIL TURBULATOR ARRANGEMENT 有权
标题翻译：涡轮空气涡轮机安装
公开(公告)号：US20160319671A1
公开(公告)日：2016-11-03
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.
摘要翻译：涡轮机翼片包括前缘和后缘。还包括冷却通道，该冷却通道在径向方向上延伸并且朝向后缘向内逐渐变细，所述冷却通道至少部分地由压力侧面和吸力侧面限定。另外包括从压力侧面和吸力侧面中的一个突出的第一多个紊流器以限定第一高度，第一多个涡流器朝向涡轮机翼型的后缘延伸并且彼此径向间隔开。还包括第二多个涡轮，其从压力侧面和吸力侧面中的一个突出，以限定小于第一高度的第二高度，第二多个涡轮朝向涡轮机翼缘的后缘延伸，彼此径向间隔开。

39. 发明申请

US20160237852A1 TORTUOUS COOLING PASSAGEWAY FOR ENGINE COMPONENT 审中-公开
标题翻译：用于发动机部件的螺旋式冷却通道
公开(公告)号：US20160237852A1
公开(公告)日：2016-08-18
申请号：US15023309
申请日：2014-09-18
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Dmitriy A. Romanov
IPC分类号： F01D25/12 , F01D11/08
CPC分类号： F01D25/12 , F01D11/08 , F01D11/24 , F05D2220/32 , F05D2230/211 , F05D2240/11 , F05D2240/12 , F05D2240/30 , F05D2250/15 , F05D2250/25 , F05D2260/202 , F05D2260/204 , F05D2260/209 , F05D2260/2214 , F05D2260/22141 , Y02T50/676
摘要： One exemplary embodiment of this disclosure relates to a gas turbine engine including a component having a body. The body includes a tortuous cooling passageway, which provides a flow path extending between an inlet in a first surface of the body and an exit in a second surface of the body.
摘要翻译：本公开的一个示例性实施例涉及一种包括具有主体的部件的燃气涡轮发动机。主体包括一个曲折的冷却通道，其提供在主体的第一表面中的入口与主体的第二表面中的出口之间延伸的流动路径。

40. 发明申请

US20160208620A1 GAS TURBINE ENGINE AIRFOIL TURBULATOR FOR AIRFOIL CREEP RESISTANCE 审中-公开
标题翻译：气体涡轮发动机空气涡轮机涡轮机抗风性能
公开(公告)号：US20160208620A1
公开(公告)日：2016-07-21
申请号：US14915455
申请日：2014-08-27
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Charles Thistle , Lane Thornton
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2220/32 , F05D2240/304 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： A gas turbine engine component includes spaced apart walls that extend in a load direction and provide a cooling passage. The cooling passage provides a tortuous passage having a generally straight portion that extends in the load direction and a bend transverse to the load direction. Elongated turbulators protrude from at least one of the walls and extend substantially in the load direction. The elongated turbulators are substantially within the generally straight portion.
摘要翻译：燃气涡轮发动机部件包括在负载方向上延伸并提供冷却通道的间隔开的壁。冷却通道提供具有在负载方向上延伸的大致直的部分和横向于负载方向的弯曲的曲折通道。细长的湍流器从至少一个壁突出并基本上在负载方向上延伸。细长的湍流器基本上在大致直的部分内。

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