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公开(公告)号：US20170342841A1
公开(公告)日：2017-11-30
申请号：US15163061
申请日：2016-05-24
Applicant: General Electric Company
Inventor： Melbourne James Myers , Xiuzhang James Zhang , Stuart Samuel Collins , Camilo Andres Sampayo , Joseph Block
IPC: F01D5/18
CPC classification number: F01D5/18 , F01D5/143 , F01D5/186 , F05D2220/32 , F05D2240/304 , F05D2240/306 , F05D2240/81 , F05D2260/20
Abstract: The present disclosure is directed to a rotor blade for a gas turbine system. The rotor blade includes a platform having a radially inner surface and a radially outer surface. A shank portion extends radially inwardly from the radially inner surface of the platform. The shank portion and the platform collectively define a shank pocket. An airfoil extends radially outwardly from the radially outer surface of the platform. The shank portion, the platform, and the airfoil collectively define a cooling passage extending from a cooling passage inlet defined by the shank portion or the platform and directly coupled to the shank pocket through the platform to a cooling passage outlet defined by the airfoil.
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公开(公告)号：US20170234142A1
公开(公告)日：2017-08-17
申请号：US15045553
申请日：2016-02-17
Applicant: General Electric Company
Inventor： Adebukola Oluwaseun Benson , Nicholas Alvin Hogberg , Xiuzhang James Zhang , Gary Michael Itzel , Mohankumar Banakar
CPC classification number: F01D5/187 , F01D5/186 , F02C3/04 , F05D2220/32 , F05D2240/304 , F05D2240/80 , F05D2250/185 , F05D2250/314 , F05D2250/38 , F05D2250/52
Abstract: The present disclosure is directed to a rotor blade for a gas turbine engine. The rotor blade includes a platform having a radially inner surface and a radially outer surface. A connection portion extends radially inwardly from the radially inner surface of the platform. An airfoil extends radially outwardly from the radially outer surface of the platform to an airfoil tip. The airfoil includes a leading edge portion and a trailing edge portion. The platform, the airfoil, and the connection portion collectively define a cooling circuit extending from an inlet defined by the connection portion to one or more outlet passages at least partially defined by the trailing edge portion of the airfoil. At least one of the one or more outlet passages include an entrance and an exit radially inwardly offset from the entrance.
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公开(公告)号：US20170204730A1
公开(公告)日：2017-07-20
申请号：US14996498
申请日：2016-01-15
Applicant: General Electric Company
CPC classification number: F01D5/187 , F01D5/143 , F01D11/006 , F02C3/04 , F05D2220/32 , F05D2240/24 , F05D2240/81 , F05D2250/185 , F05D2260/201 , F05D2260/205
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.
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Patent Agency Ranking
公开(公告)号：US20170152752A1
公开(公告)日：2017-06-01
申请号：US14955563
申请日：2015-12-01
Applicant: General Electric Company
Inventor： Melbourne James Myers , Camilo Andres Sampayo , Xiuzhang James Zhang
CPC classification number: F01D5/187 , F01D5/082 , F01D5/147 , F05D2240/304 , F05D2240/80 , F05D2260/20 , Y02T50/676
Abstract: A turbomachine blade is disclosed including an airfoil including a cooling fluid plenum extending therein and a trailing edge cooling opening extending from the cooling fluid plenum through a trailing edge of the airfoil. A platform may couple the airfoil to a shank, the platform including a trailing edge root extending downstream relative to the shank. At least one cooling conduit delivers a cooling fluid radially inward from at least one of the cooling fluid plenum and the trailing edge cooling opening to a wheel space that is adjacent the shank and radially inward from the trailing edge root. A related turbomachine is also disclosed.
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公开(公告)号：US20160319671A1
公开(公告)日：2016-11-03
申请号：US14699607
申请日：2015-04-29
Applicant: General Electric Company
Inventor： Adebukola Oluwaseun Benson , Nicholas Alvin Hogberg , Gary Michael Itzel , Mitchell Allan Merrill , Xiuzhang James Zhang
IPC: F01D5/18
CPC classification number: F01D5/18 , F01D5/187 , F05D2240/127 , F05D2260/2212 , F05D2260/22141
Abstract: 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.
Abstract translation: 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。
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公开(公告)号：US20160258302A1
公开(公告)日：2016-09-08
申请号：US14639374
申请日：2015-03-05
Applicant: General Electric Company
Inventor： Adebukola Oluwaseun Benson , Lisa De Bellis , Xiuzhang James Zhang
CPC classification number: F01D5/20 , F01D5/02 , F01D5/187 , F01D5/3007 , F05D2220/31 , F05D2230/60 , F05D2240/12 , F05D2240/307 , F05D2250/711 , F05D2250/712 , F05D2260/20
Abstract: An airfoil includes a squealer tip at an outer radial end of the airfoil. A squealer tip pocket of the squealer tip has a convex side and a concave side, and a tip plate. A divider extends across the tip plate from the concave side to the convex side to divide the squealer tip pocket into a first pocket and a second pocket. At least one cooling passage through the tip plate in the second pocket provides fluid communication through the tip plate from an interior of the airfoil to the second pocket. The first pocket is fluidically disconnected from the interior of the airfoil.
Abstract translation: 机翼包括在翼型件的外径向端部处的尖叫尖端。 尖叫尖端的尖叫尖端口具有凸面和凹面，以及尖端板。 分隔件从凹入侧延伸穿过顶板至凸侧，以将尖叫尖端口分成第一口袋和第二口袋。 通过第二口袋中的顶板的至少一个冷却通道提供从翼型件的内部到第二口袋的通过顶板的流体连通。 第一口袋与翼型件的内部在流体上断开连接。
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公开(公告)号：US09121292B2
公开(公告)日：2015-09-01
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。
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公开(公告)号：US20140161625A1
公开(公告)日：2014-06-12
申请号：US13711241
申请日：2012-12-11
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Xiuzhang James Zhang , Adebukola Oluwaseun Benson , Richard Ryan Pilson , Stephen William Tesh
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2230/11 , F05D2250/232 , F05D2250/25 , F05D2250/323
Abstract: Systems and devices configured to cool turbine components in a turbine by passing a cooling flow through the turbine component via a cooling passage with a variable diameter are disclosed. In one embodiment, a turbine component includes: at least one elongated cooling passage extending from a root of the bucket to a tip of the bucket, wherein the elongated cooling passage has a variable diameter along a length of the bucket.
Abstract translation: 公开了通过使冷却流通过涡轮机部件经由具有可变直径的冷却通道来冷却涡轮机中的涡轮机部件的系统和装置。 在一个实施例中，涡轮机部件包括：从铲斗的根部延伸到铲斗的尖端的至少一个细长的冷却通道，其中细长的冷却通道沿铲斗的长度具有可变的直径。
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