公开(公告)号：US20170107829A1

公开(公告)日：2017-04-20

申请号：US14884114

申请日：2015-10-15

Applicant: General Electric Company

Inventor： Matthew Lee Krumanaker ,  Steven Robert Brassfield ,  Robert Frederick Bergholz ,  Aaron Ezekiel Smith ,  Weston Nolan Dooley

IPC: F01D5/18 ,  F01D25/12 ,  F01D5/30 ,  F01D9/04

CPC classification number: F01D5/187 ,  F01D5/3007 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/221 ,  Y02T50/676

Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuits can be fed with a flow of cooling fluid from one or more cooling air inlet passages in fluid communication with the cooling circuits. The cooling circuits can further comprise a leading edge cooling circuit defined by a supply passage, a pin bank passage divided into one or more sub-circuits by pin banks disposed within the pin bank passage, and at least first and second cooling passages. The cooling circuits can provide the cooling fluid flow within the airfoil to cool the airfoil, as well as provide a cooling fluid to a plurality of film holes to create a cooling film on the external surface of the airfoil.

公开(公告)号：US20160186660A1

公开(公告)日：2016-06-30

申请号：US14587534

申请日：2014-12-31

Applicant: General Electric Company

Inventor： Robert Frederick Bergholz ,  Aaron Ezekiel Smith

IPC: F02C7/18 ,  F01D5/18

CPC classification number: F02C7/18 ,  F01D5/18 ,  F01D5/187 ,  F05D2250/20 ,  F05D2260/2212 ,  F05D2260/22141 ,  F23R3/16 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

Abstract: An engine component includes a hot surface in thermal communication with a hot combustion gas flow, and a cooling surface, opposite the hot surface, along which a cooling fluid flows. At least one vortex generator is provided on the cooling surface, and can induce a vortex in the cooling fluid in response to contact with the flowing cooling fluid.

Abstract translation: 发动机部件包括与热燃烧气流热连通的热表面，以及与热表面相对的冷却表面，冷却流体沿着冷却表面流动。 至少一个涡流发生器设置在冷却表面上，并可响应于与流动的冷却流体的接触而在冷却流体中引起涡流。

公开(公告)号：US09249675B2

公开(公告)日：2016-02-02

申请号：US14453366

申请日：2014-08-06

Applicant: General Electric Company

Inventor： Aaron Ezekiel Smith

IPC: F01D5/18

CPC classification number: F01D5/188 ,  F05D2240/304 ,  F05D2260/2212 ,  F05D2260/2214

Abstract: The present application provides an airfoil with a cooling flow therein. The airfoil may include an internal cooling passage, a number of cooling holes in communication with the internal cooling passage, and a number of pin-fins positioned within the internal cooling passage. The pin-fins are arranged with one or more turning openings and one or more guiding openings so as to direct the cooling flow towards the cooling holes.

Abstract translation: 本申请提供其中具有冷却流的翼型件。 翼型件可以包括内部冷却通道，与内部冷却通道连通的多个冷却孔以及位于内部冷却通道内的多个销翅片。 销翅片布置有一个或多个转动开口和一个或多个引导开口，以便将冷却流引向冷却孔。

公开(公告)号：US20150218962A1

公开(公告)日：2015-08-06

申请号：US14173949

申请日：2014-02-06

Applicant: General Electric Company

Inventor： David Wayne Weber ,  Gregory Thomas Foster ,  Benjamin Paul Lacy ,  Aaron Ezekiel Smith ,  Dustin Michael Earnhardt

IPC: F01D25/12 ,  B22C7/02 ,  B22C9/10 ,  B22C9/24 ,  B22C9/04

CPC classification number: B22C7/02 ,  B22C9/04 ,  B22C9/10 ,  B22C9/103 ,  B22C9/108 ,  B22C9/24 ,  F01D5/186 ,  F05D2230/211 ,  F05D2240/81 ,  F05D2260/204

Abstract: A core for forming micro channels within a turbine component is provided. The core includes a base comprising a first side and a second side; and a core assembly coupled to the second side. The core assembly further includes a plurality of channel members, wherein each channel member has a first end, a second end, and a channel body coupled to and extending between said first end and said second end. The channel body includes a channel shape configured to form the micro channels within the turbine component.

Abstract translation: 提供了一种用于在涡轮机部件内形成微通道的芯。 芯部包括一个包括第一面和第二面的基底; 以及耦合到第二侧的芯组件。 芯组件还包括多个通道构件，其中每个通道构件具有第一端，第二端和与所述第一端和所述第二端连接并在其之间延伸的通道体。 通道体包括被配置为在涡轮部件内形成微通道的通道形状。

公开(公告)号：US20150184538A1

公开(公告)日：2015-07-02

申请号：US14143508

申请日：2013-12-30

Applicant: General Electric Company

Inventor： Aaron Ezekiel Smith

IPC: F01D25/12

CPC classification number: F01D25/12 ,  F01D5/186 ,  F01D5/187 ,  F05D2260/201 ,  Y02T50/676

Abstract: An airfoil of a turbine rotor blade that includes a cooling configuration having a plurality of elongated flow passages for receiving and directing a coolant along a path through the airfoil. The cooling configuration may include: a central flow passage flanked to each side by near-wall flow passages that includes a pressure side near-wall flow passage and a suction side near-wall flow passage; a first port that fluidly connects the central flow passage to the pressure side near-wall flow passage; a second port that fluidly connects the central flow passage to the suction side near-wall flow passage; and impingement connectors that fluidly connect the central flow passage to a leading edge flow passage.

Abstract translation: 涡轮转子叶片的翼型件，其包括具有多个细长流动通道的冷却构造，用于沿着通过翼型的路径接收和引导冷却剂。 冷却结构可以包括：通过近壁流动通道在每侧的侧面的中央流动通道，其包括压力侧近壁流动通道和吸力侧近壁流动通道; 第一端口，其将中央流动通道流体连接到压力侧近壁流动通道; 第二端口，其将中央流动通道流体连接到吸入侧近壁流动通道; 以及冲击连接器，其将中央流动通道流体连接到前缘流动通道。

公开(公告)号：US20150184525A1

公开(公告)日：2015-07-02

申请号：US14143537

申请日：2013-12-30

Applicant: General Electric Company

Inventor： Aaron Ezekiel Smith ,  Lisa Anne Wichmann

IPC: F01D5/18

CPC classification number: F01D5/188 ,  F01D5/187 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2250/71 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2250/713 ,  F05D2250/75 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A turbine blade that includes an airfoil defined by a concave shaped pressure side outer wall and a convex shaped suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The turbine blade further may include a rib configuration that partitions the chamber of the airfoil into radially extending flow passages. A first flow passage may include a first side on which turbulators are positioned, wherein each of the turbulators comprises a canted configuration.

Abstract translation: 一种涡轮机叶片，其包括由凹形压力侧外壁和凸形吸入侧外壁限定的翼型件，所述翼型件沿着前缘和后缘连接，并且在其间形成用于接收冷却剂流的径向延伸的室。 涡轮叶片还可以包括将翼型腔分成径向延伸的流动通道的肋构型。 第一流动通道可以包括其上定位有湍流器的第一侧，其中每个湍流器包括倾斜构造。

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。