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公开(公告)号：US20150184519A1
公开(公告)日：2015-07-02
申请号：US14143443
申请日：2013-12-30
Applicant: General Electric Company
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/188 , F05D2240/305 , F05D2240/306 , F05D2250/71 , F05D2250/711 , F05D2250/712 , F05D2250/713 , F05D2250/75 , F05D2260/22141 , Y02T50/676
Abstract: A turbine blade having 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 may further include a rib configuration that partitions the chamber into radially extending flow passages. The rib configuration may include a camber line rib having a wavy profile. The wavy profile may include at least one back-and-forth “S” shape.
Abstract translation: 一种具有由凹形压力侧外壁和凸形吸入侧外壁限定的翼型件的涡轮机叶片，其沿着前缘和后缘连接，并且在它们之间形成用于接收冷却剂流动的径向延伸室。 涡轮叶片还可以包括将腔室分隔成径向延伸的流动通道的肋构型。 肋构造可以包括具有波浪形轮廓的弧形线肋。 波浪形轮廓可以包括至少一个前后“S”形。
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62.发明申请公开(公告)号：US20150118022A1
公开(公告)日：2015-04-30
申请号：US14064918
申请日：2013-10-28
Applicant: General Electric Company
Inventor： David Wayne WEBER , Gregory Thomas Foster , Aaron Ezekiel Smith
CPC classification number: F01D11/24 , F01D9/04 , F01D11/005 , F05D2240/11 , F05D2240/81 , F05D2260/205
Abstract: In one example, an arcuate segment for a ring-shaped, rotary machine component such as a stator nozzle or bucket shroud, includes a segment body having an end face formed with a circumferentially-facing seal slot adapted to receive a seal extending between the segment body and a corresponding seal slot in an adjacent segment body to seal a radially-extending gap between the adjacent segment bodies. A cooling channel is provided in the segment body in proximity to the seal slot, and is adapted to be supplied with cooling air. A passage extends from the cooling channel into the seal slot, at a location where the cooling air can be supplied to the higher pressure area on the radially-outer side of the seal.
Abstract translation: 在一个示例中，用于环形旋转机器部件（例如定子喷嘴或铲斗护罩）的弧形段包括段体，其具有形成有面向周向的密封槽的端面，其适于接收在段 主体和相邻的分段体中相应的密封槽，以密封相邻分段体之间的径向延伸的间隙。 冷却通道设置在分段主体中，靠近密封槽，并且适于供应冷却空气。 通道从冷却通道延伸到密封槽中，在冷却空气可被供应到密封件的径向外侧上的较高压力区域的位置处。
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公开(公告)号：US11732593B2
公开(公告)日：2023-08-22
申请号：US17519038
申请日：2021-11-04
Applicant: General Electric Company
CPC classification number: F01D5/187 , F01D9/041 , F05D2240/121 , F05D2240/303 , F05D2250/18 , F05D2260/201 , F05D2260/202 , F05D2260/22141 , Y02T50/60
Abstract: A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and form a radially extending chamber for receiving a coolant flow. A rib configuration may include: a leading edge transverse rib connecting the pressure side outer wall and the suction side outer wall and partitioning the radially extending chamber into a leading edge passage within the leading edge of the airfoil and a central passage adjacent to the leading edge passage. One or both camber line ribs connect to a corresponding pressure side outer wall and suction side outer wall at a point aft of the leading edge transverse rib causing the central passage to extend towards one or both of the pressure side outer wall and the suction side outer wall, resulting in a flared center cavity aft of the leading edge.
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公开(公告)号：US20220056805A1
公开(公告)日：2022-02-24
申请号：US17519038
申请日：2021-11-04
Applicant: General Electric Company
Abstract: A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and form a radially extending chamber for receiving a coolant flow. A rib configuration may include: a leading edge transverse rib connecting the pressure side outer wall and the suction side outer wall and partitioning the radially extending chamber into a leading edge passage within the leading edge of the airfoil and a central passage adjacent to the leading edge passage. One or both camber line ribs connect to a corresponding pressure side outer wall and suction side outer wall at a point aft of the leading edge transverse rib causing the central passage to extend towards one or both of the pressure side outer wall and the suction side outer wall, resulting in a flared center cavity aft of the leading edge.
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公开(公告)号：US10208608B2
公开(公告)日：2019-02-19
申请号：US15239968
申请日：2016-08-18
Applicant: General Electric Company
Abstract: A cooling circuit according to an embodiment includes: a cooling circuit for a multi-wall blade, the cooling circuit including: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a central cavity disposed between the pressure side and suction side cavities, the central cavity including no surfaces adjacent the pressure and suction sides of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade; and at least one impingement opening for fluidly coupling the first leading edge cavity with a second leading edge cavity.
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Patent Agency Ranking
公开(公告)号：US10094570B2
公开(公告)日：2018-10-09
申请号：US14567768
申请日：2014-12-11
Applicant: General Electric Company
Inventor： Lewis Berkley Davis, Jr. , Gregory Thomas Foster , Kaitlin Marie Graham , Krishnakumar Venkataraman , Stanley Kevin Widener
Abstract: Aspects of the present disclosure provide an apparatus including: an injector in fluid communication with an aft section of a reheat combustor in a power generation system, the aft section being positioned downstream of a combustion reaction zone in the reheat combustor, and positioned upstream of a turbine stage of the power generation system, wherein the turbine stage includes a turbine nozzle and a turbine blade row; and a conduit in fluid communication with the injector, wherein the conduit delivers at least one of a fuel from a fuel supply line and a carrier gas to the injector.
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公开(公告)号：US10053990B2
公开(公告)日：2018-08-21
申请号：US15152707
申请日：2016-05-12
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster , Michelle Jessica Iduate , Brendon James Leary , Jacob Charles Perry, II
CPC classification number: F01D5/187 , F01D5/141 , F01D5/147 , F01D9/02 , F01D25/12 , F05D2220/32 , F05D2240/305 , F05D2240/306 , F05D2250/14 , F05D2250/185 , F05D2250/711 , F05D2250/712 , F05D2260/201 , F05D2260/202 , F05D2260/22141 , Y02T50/676
Abstract: An internal rib for a blade airfoil has a concave surface defined to ensure durability and provide desired heat transfer. A concave surface faces a pressure side or suction side outer wall. A width is between a first end and a second end, and a depth is a length of a normal depth line between a midpoint of the concave surface and an intersection point of the depth line with the pressure or suction side outer wall. An irregular arc is defined within an arc angle centered at the intersection point, the irregular arc has a first arc radius equivalent to the depth at the midpoint of the concave surface and a second arc radius where the arc angle intersects the concave surface equivalent to a product of the depth and a shape factor. The shape factor has a substantially linear relationship with the aspect ratio.
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公开(公告)号：US10052683B2
公开(公告)日：2018-08-21
申请号：US14977028
申请日：2015-12-21
Applicant: General Electric Company
Inventor： Gregory Thomas Foster , David Wayne Weber , Michelle Jessica Iduate , Brendon James Leary , Joseph Anthony Weber
CPC classification number: B22C9/103 , B22C9/108 , B22C9/12 , B22C9/24 , B22C21/14 , F01D5/187 , F05D2220/32 , F05D2230/21 , F05D2260/20 , G01B17/02 , G01B21/08
Abstract: A core for a turbine airfoil casting according to an embodiment includes: a center plenum section; and a plurality of outer passage sections; wherein the center plenum section includes at least one boss extending outwardly from the center plenum to an outer profile of the core.
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公开(公告)号：US20180112547A1
公开(公告)日：2018-04-26
申请号：US15334450
申请日：2016-10-26
Applicant: General Electric Company
Inventor： Zachary John Snider , Gregory Thomas Foster , Joseph Anthony Weber , James Fredric Wiedenhoefer
CPC classification number: F01D9/065 , F01D5/147 , F01D5/186 , F01D5/187 , F01D9/041 , F01D9/06 , F01D25/08 , F05D2220/32 , F05D2240/122 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2260/202 , F05D2260/204
Abstract: A turbine airfoil for a rotating blade or stationary nozzle vane includes an airfoil body including a leading edge and a trailing edge. A coolant supply passage extends within the airfoil body, and a coolant return passage extends within the airfoil body. A first trench is in an external surface of the airfoil body, the first trench extending to the trailing edge and being in fluid communication with the coolant supply passage. A second trench is in the external surface of the airfoil body, the second trench extending to the trailing edge and being in fluid communication with the coolant return passage and the first trench. A cover seats in the airfoil body and encloses the trenches to form coolant passages with the airfoil body. In embodiments, two coolant passages to and back from the trailing edge may be used to allow for a recycling flow.
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公开(公告)号：US20180112534A1
公开(公告)日：2018-04-26
申请号：US15334483
申请日：2016-10-26
Applicant: General Electric Company
CPC classification number: F01D5/147 , F01D5/187 , F01D5/286 , F05D2240/304
Abstract: A turbine airfoil for a rotating blade or stationary nozzle vane includes an airfoil body including a leading edge and a trailing edge. A coolant supply passage extends within the airfoil body and a coolant return passage extends within the airfoil body, with each passage having respective a supply and return connection passage to an exterior surface of the airfoil body. A seat in the exterior surface of the airfoil body receives a cover that includes a trench on an interior surface thereof to fluidly connect the return connection passage and the supply connection passage and form a coolant passage for the airfoil body. Various arrangements of cooling circuits may be created with the cover that allow for reuse of the coolant.
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