-
公开(公告)号：US20150345303A1
公开(公告)日：2015-12-03
申请号：US14288748
申请日：2014-05-28
Applicant: General Electric Company
Inventor： Zhirui Dong , Xiuzhang James Zhang , Jason Adam Neville
IPC: F01D5/18
CPC classification number: F01D5/186 , F01D5/085 , F01D5/187 , F05D2260/202 , F05D2260/2212 , Y02T50/676
Abstract: A rotor blade includes a mounting portion comprising a mounting body that is formed to receive a coolant therein. An airfoil portion extends substantially radially outwardly from the mounting body and includes an airfoil body. The mounting body and the airfoil body define a plurality of primary cooling passages that extend substantially radially therein for routing the coolant through the airfoil body. Each of the primary cooling passages includes a cooling flow outlet that is formed along a tip portion of the airfoil body. The airfoil body further defines a plurality of trailing edge cooling passages, each having a coolant outlet that is formed along a trailing edge portion of the airfoil body. At least a portion of the trailing edge cooling passages are formed along a radially outer portion of the trailing edge proximate to the tip portion of the airfoil body.
Abstract translation: 转子叶片包括安装部分，其包括形成为在其中容纳冷却剂的安装体。 机翼部分从安装体基本上径向向外延伸并且包括翼型体。 安装体和翼型体限定了多个基本上径向延伸的主冷却通道，用于使冷却剂穿过翼型体。 每个主冷却通道包括沿翼型本体的尖端部分形成的冷却流出口。 翼型体还限定多个后缘冷却通道，每个后缘冷却通道具有沿翼型本体的后缘部分形成的冷却剂出口。 尾缘冷却通道的至少一部分沿靠近翼型本体的尖端部分的后缘的径向外部部分形成。
-
公开(公告)号：US10196903B2
公开(公告)日：2019-02-05
申请号：US14996498
申请日：2016-01-15
Applicant: General Electric Company
Abstract: The present disclosure is directed to a rotor blade for a gas turbine engine. The rotor blade includes a platform comprising a radially inner surface, an undulating radially outer surface, a leading edge portion, a trailing edge portion, a pressure-side slash face, and a suction-side slash face. An airfoil extends outwardly from the undulating radially outer surface of the platform to an airfoil tip. A connection portion extends radially inwardly from the radially inner surface of the platform. The platform, the airfoil, and the connection portion collectively define a cooling circuit extending from an inlet in the connection portion through the airfoil to a plurality of outlet plena in the platform. Two or more outlet plena of the plurality of outlet plena are spaced equidistant from the undulating radially outer surface of the platform.
-
公开(公告)号：US10138735B2
公开(公告)日：2018-11-27
申请号：US14932104
申请日：2015-11-04
Applicant: General Electric Company
Inventor： Adebukola Oluwaseun Benson , Xiuzhang James Zhang , Nicholas Alvin Hogberg , Kenneth Earl Williams
Abstract: In one aspect of the present disclosure, an airfoil for a rotor blade of a gas turbine includes a normalized pressure side wall portion thickness, a normalized suction side wall portion thickness, a normalized leading edge wall thickness, and a normalized trailing edge wall thickness. The values of theses thicknesses define the pressure side wall portion thickness, the suction side wall portion thickness, the leading edge wall thickness, and the trailing edge wall thickness, which improve heat transfer, flow distribution, and mechanical load transfer.
-
公开(公告)号：US20170122111A1
公开(公告)日：2017-05-04
申请号：US14932104
申请日：2015-11-04
Applicant: General Electric Company
Inventor： Adebukola Oluwaseun Benson , Xiuzhang James Zhang , Nicholas Alvin Hogberg , Kenneth Earl Williams
IPC: F01D5/18
CPC classification number: F01D5/188 , F01D5/147 , F05D2260/201
Abstract: In one aspect of the present disclosure, an airfoil for a rotor blade of a gas turbine includes a normalized pressure side wall portion thickness, a normalized suction side wall portion thickness, a normalized leading edge wall thickness, and a normalized trailing edge wall thickness. The values of theses thicknesses define the pressure side wall portion thickness, the suction side wall portion thickness, the leading edge wall thickness, and the trailing edge wall thickness, which improve heat transfer, flow distribution, and mechanical load transfer.
-
公开(公告)号：US20150345301A1
公开(公告)日：2015-12-03
申请号：US14289908
申请日：2014-05-29
Applicant: General Electric Company
Inventor： Xiuzhang James Zhang , James William Vehr , Haiping Wang
IPC: F01D5/18
CPC classification number: F01D5/18 , F01D5/20 , Y02T50/673
Abstract: A rotor blade includes and airfoil. The airfoil includes pressure and suction side walls which extend radially outwardly from a platform in span from a root to a tip and between a leading edge and a trialing edge. The tip includes a tip floor, a plurality of coolant outlets and a tip rail having a pressure side and suction side portions that extend radially outwardly from the tip floor. Cooling passages are circumscribed within the airfoil and are in fluid communication with one or more of the coolant outlets. A baffle extends radially outwardly from and transversely across the tip floor from the pressure side portion to the suction side portion to define first and second tip pockets. A slot is disposed along the suction side portion of the tip rail to provide for fluid communication out of one of the first or second tip pockets, thereby reducing pressure within the corresponding tip pocket.
Abstract translation: 转子叶片包括和翼型。 翼型件包括压力和抽吸侧壁，其从跨度从平台的平台径向向外延伸，从根部到尖端以及前缘和修剪边缘之间。 尖端包括尖端底板，多个冷却剂出口和尖端轨道，其具有从尖端底部径向向外延伸的压力侧和吸力侧部分。 冷却通道在翼型内限定，并与一个或多个冷却剂出口流体连通。 挡板从顶部地板从压力侧部分径向向外并横向延伸穿过吸力侧部分，以限定第一和第二尖端口袋。 沿着尖端轨道的吸力侧部分设置槽以提供从第一或第二尖端口中的一个流体连通，从而减小对应的尖端口袋内的压力。
-
Patent Agency Ranking
公开(公告)号：US20140154063A1
公开(公告)日：2014-06-05
申请号：US13705804
申请日：2012-12-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Xiuzhang James Zhang , Stephen Paul Wassynger , Aaron Ezekiel Smith , Anthony Louis Giglio
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/186 , F05D2240/81 , Y02T50/673 , Y02T50/676
Abstract: An airfoil includes an outer surface having a leading edge, a trailing edge downstream from the leading edge, and a convex surface between the leading and trailing edges. A cavity is inside the outer surface, and a platform is connected to the outer surface and defines a top surface around at least a portion of the outer surface. A first plurality of trenches is beneath the top surface of the platform upstream from the leading edge, wherein each trench in the first plurality of trenches is in fluid communication with the cavity inside the outer surface. A first plurality of cooling passages provide fluid communication from the first plurality of trenches through the top surface of the platform.
Abstract translation: 翼型件包括具有前缘的外表面，在前缘下游的后缘以及前缘和后缘之间的凸面。 空腔在外表面内，并且平台连接到外表面并且围绕外表面的至少一部分限定顶表面。 第一多个沟槽位于平台的顶表面上方的前缘上游，其中第一多个沟槽中的每个沟槽与外表面内的空腔流体连通。 第一多个冷却通道提供从第一多个沟槽通过平台的顶表面的流体连通。
-
公开(公告)号：US20140099193A1
公开(公告)日：2014-04-10
申请号：US13645585
申请日：2012-10-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Xiuzhang James Zhang , Adebukola Benson , Zhirui Dong
CPC classification number: F01D5/20
Abstract: A rotor blade includes an airfoil having a tip plate that extends across an outer radial end. A rim extends radially outward from the tip plate and surrounds at least a portion of the airfoil and includes a concave portion opposed to a convex portion. A plurality of dividers extend between the concave and convex portions to define a plurality of pockets between the concave and convex portions at the outer radial end. A plurality of cooling passages through the tip plate provide fluid communication through the tip plate to the plurality of pockets. A first fluid passage in at least one divider provides fluid communication between adjacent pockets across the at least one divider.
Abstract translation: 转子叶片包括具有延伸穿过外径向端的顶板的翼型件。 边缘从顶板径向向外延伸并且包围翼型的至少一部分并且包括与凸部相对的凹部。 多个分隔件在凹部和凸部之间延伸以在外径向端部处在凹部和凸部之间限定多个凹穴。 通过顶板的多个冷却通道提供通过顶板到多个凹穴的流体连通。 至少一个分隔器中的第一流体通道提供穿过至少一个分隔器的相邻袋之间的流体连通。
-
公开(公告)号：US10184342B2
公开(公告)日：2019-01-22
申请号：US15099116
申请日：2016-04-14
Applicant: General Electric Company
Inventor： Xiuzhang James Zhang , James Tyson Balkcum, III , Ian Darnall Reeves , Joseph Anthony Cotroneo
Abstract: A turbine blade includes a tip shroud having a seal rail. The seal rail includes a tangential surface extending between tangential ends. The turbine blade includes a root portion configured to couple to a rotor and an airfoil portion extending between the root portion and the tip shroud. The seal rail includes a cooling passage extending along a length of the seal rail. The cooling passage is fluidly coupled to a cooling plenum to receive a cooling fluid via an intermediate cooling passage extending between the cooling passage and a cooling plenum. The seal rail includes cooling outlet passages fluidly coupled to the cooling passage. The cooling outlet passages are disposed within the seal rail and extend between the cooling passage and the tangential surface of the seal rail. The cooling outlet passages are configured to discharge the cooling fluid from the tip shroud via the tangential surface.
-
公开(公告)号：US10107108B2
公开(公告)日：2018-10-23
申请号：US14699321
申请日：2015-04-29
Applicant: General Electric Company
Inventor： Jeffrey Clarence Jones , Xiuzhang James Zhang , Mitchell Allan Merrill
Abstract: 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.
-
公开(公告)号：US20180171802A1
公开(公告)日：2018-06-21
申请号：US15383228
申请日：2016-12-19
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , Kassy Moy Hart , Xiuzhang James Zhang
CPC classification number: 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
Abstract: 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.
-
-
-
-
-
-
-
-
-
Search Results
38
records
(took 0.021 seconds)
