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公开(公告)号：US20210003020A1
公开(公告)日：2021-01-07
申请号：US17029807
申请日：2020-09-23
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Gregory Terrence Garay , Tingfan Pang , Helen Ogbazion Gabregiorgish , Zachary Daniel Webster , Steven Robert Brassfield
Abstract: An apparatus and method an engine component for a turbine engine comprising an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides extending between a leading edge and a trailing edge to define a chord-wise direction, and extending between a root and a tip to define a span-wise direction, at least one cooling passage located within the interior, a set of cooling holes having an inlet fluidly coupled to the cooling passage, an outlet located on one of the pressure side or suction side, with a connecting passage fluidly coupling the inlet to the outlet.
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公开(公告)号：US10738621B2
公开(公告)日：2020-08-11
申请号：US16059212
申请日：2018-08-09
Applicant: General Electric Company
Inventor： Stephen Mark Molter , Mark Edward Stegmiller , Shawn Michael Pearson , Steven Robert Brassfield
Abstract: A turbine airfoil apparatus includes: an airfoil including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and at a trailing edge; an endwall that projects laterally outwardly from the airfoil at one spanwise end thereof, the endwall having an outer surface facing the airfoil and an opposing inner surface; a plenum defined within the endwall between the inner and outer surfaces wherein the plenum is forked in plan view, with at least two branches, each branch terminating at a closed end, each branch having a throat disposed at its upstream end, wherein each throat has a relatively constricted flow area for increasing flow velocity; and at least one film cooling hole passing through the outer surface and communicating with the plenum.
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公开(公告)号：US20200024951A1
公开(公告)日：2020-01-23
申请号：US16037662
申请日：2018-07-17
Applicant: GENERAL ELECTRIC COMPANY
Inventor： William Charles Herman , Jacob Romeo Rendon , Duane Allan Busch , Ryan Christopher Jones , Paul Christopher Schilling , Zachary Daniel Webster , Tingfan Pang , Gregory Terrence Garay , Steven Robert Brassfield
IPC: F01D5/08
Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The cooling hole can extend from an inlet to an outlet to define a passage. The cooling hole can include a laid back section where a coating can be applied. The method can include forming the cooling hole in the component and applying the coating to the component to maintain a specific geometry.
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公开(公告)号：US20190257205A1
公开(公告)日：2019-08-22
申请号：US15898716
申请日：2018-02-19
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Zachary Daniel Webster , Gregory Terrence Garay , Kevin Robert Feldmann , Steven Robert Brassfield
Abstract: An apparatus and method an engine component for a turbine engine comprising an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides extending between a leading edge and a trailing edge to define a chord-wise direction, and extending between a root and a tip to define a span-wise direction, at least one cooling passage located within the interior, at least one cooling hole having an inlet fluidly coupled to the cooling passage and an outlet located along the outer wall.
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公开(公告)号：US10370978B2
公开(公告)日：2019-08-06
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
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.
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Patent Agency Ranking
公开(公告)号：US20180291743A1
公开(公告)日：2018-10-11
申请号：US15481659
申请日：2017-04-07
Applicant: General Electric Company
Inventor： James Michael Hoffman , Weston Nolan Dooley , Matthew Lee Krumanaker , Aaron Ezekiel Smith , Steven Robert Brassfield
Abstract: A turbine engine can include an airfoil comprising an outer wall bounding an interior, as well as an airfoil cooling circuit located within the interior and including a feed tube separating into at least first and second branches. A flow divider can be included in the airfoil and positioned to confront the feed tube.
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公开(公告)号：US09840920B2
公开(公告)日：2017-12-12
申请号：US14407867
申请日：2013-06-14
Applicant: General Electric Company
Inventor： Shawn Michael Pearson , Steven Robert Brassfield , Mark Edward Stegemiller , Jonathan Filipa , Daniel Lee Durstock
CPC classification number: F01D5/30 , F01D5/22 , F01D5/3015 , F01D11/00 , F01D11/006 , F05D2240/57 , Y10T29/49321
Abstract: A rotor assembly for use in a gas turbine engine having an axis of rotation includes a plurality of rotor blades. Each rotor blade includes a platform extending between opposing side faces, a shank extending radially inward from the platform, and a slot at least partially defined in each of the opposing side faces. A sealing member is configured to be inserted into each slot of a first rotor blade of the plurality of rotor blades such that at least a portion of each sealing member extends beyond one of the opposing side faces. A second rotor blade of the plurality of rotor blades is coupled adjacent the first rotor blade such that at least a portion of one sealing member is inserted into a corresponding second slot on the second rotor blade.
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公开(公告)号：US20170107826A1
公开(公告)日：2017-04-20
申请号：US14884075
申请日：2015-10-15
Applicant: General Electric Company
Inventor： Matthew Lee Krumanaker , Weston Nolan Dooley , Steven Robert Brassfield , David Benjamin Helmer , Jeremy Clyde Bailey , Robert David Briggs
CPC classification number: F01D5/187 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2260/202 , F05D2260/204 , Y02T50/676
Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuit can further comprise a near wall cooling mesh, fluidly coupling a supply passage to a mesh plenum. The mesh plenum can be disposed adjacent to the external surface of the airfoil having a plurality of film holes extending between the mesh plenum and the external surface of the airfoil. The mesh plenum can further comprise a cross-sectional area sized to facilitate machining of the film holes without damage to the interior of the airfoil.
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公开(公告)号：US20150152735A1
公开(公告)日：2015-06-04
申请号：US14406018
申请日：2013-06-17
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Stephen Mark Molter , Mark Edward Stegemiller , Shawn Michael Pearson , Steven Robert Brassfield
CPC classification number: F01D5/186 , B23P15/02 , F01D5/187 , F01D5/20 , F01D5/225 , F01D9/041 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2240/81 , F05D2260/202 , Y10T29/49341
Abstract: A turbine airfoil apparatus includes: an airfoil including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and a trailing edge; an endwall projecting laterally outwardly from the airfoil at one spanwise end thereof, the endwall having an outer surface facing the airfoil and an opposing inner surface; a plenum defined within the endwall between the inner and outer surfaces wherein the plenum is forked in plan view, with at least two branches, each branch having a throat disposed at its upstream end; and at least one film cooling hole passing through the outer surface and communicating with the plenum.
Abstract translation: 涡轮机翼型装置包括：在前缘和后缘处连接在一起的包括凹压侧壁和凸吸吸侧壁的翼型件; 所述端壁在所述翼型件的一个翼展端处从所述翼型件横向向外突出，所述端壁具有面向所述翼型件的外表面和相对的内表面; 限定在内表面和外表面之间的端壁内的气室，其中气室在平面图中分叉，至少两个分支，每个分支具有设置在其上游端的喉部; 以及至少一个通过外表面并与气室连通的薄膜冷却孔。
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公开(公告)号：US11885236B2
公开(公告)日：2024-01-30
申请号：US17714629
申请日：2022-04-06
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F01D5/187 , F01D5/20 , F01D5/3007 , F05D2240/304 , F05D2240/305 , F05D2240/306 , F05D2240/307 , F05D2240/81 , F05D2260/201 , F05D2260/202
Abstract: An airfoil for a turbine engine includes an outer wall bounding an interior and defining a pressure side and a suction side, the outer wall extending axially between a leading edge and a trailing edge to define a chord-wise direction, and also extending radially between a root and a tip to define a span-wise direction. At least one cooling conduit can be formed in the interior of the airfoil, and a tip rail can project from the tip in the span-wise direction.
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