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公开(公告)号：US10697301B2
公开(公告)日：2020-06-30
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：US10590778B2
公开(公告)日：2020-03-17
申请号：US15667787
申请日：2017-08-03
Applicant: General Electric Company
Inventor： Emily Rosette Clark , Weston Nolan Dooley , Kirk D. Gallier
Abstract: An apparatus and method for cooling an engine component such as an airfoil can include an outer wall separating a cooling fluid flow from a hot flow. A cooling circuit can be provided in the engine component including a cooling passage having at least one pin within the cooling passage with a chevron shape and a non-uniform configuration.
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Patent Agency Ranking
公开(公告)号：US10443403B2
公开(公告)日：2019-10-15
申请号：US15412387
申请日：2017-01-23
Applicant: General Electric Company
Inventor： Weston Nolan Dooley , James Michael Hoffman , Steven Robert Brassfield
Abstract: An apparatus relating to engineering the geometry for a ball-chute support feature in an investment casting core. The investment casting core is for an airfoil region having at least one serpentine feature and at least one inlet feature coupled to the at least one serpentine feature by a ball-chute support feature. The investment casting core is leached out to form cooling passages in the airfoil.
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公开(公告)号：US10208605B2
公开(公告)日：2019-02-19
申请号：US14884009
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: A turbine engine comprises an airfoil having 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 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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公开(公告)号：US20190040748A1
公开(公告)日：2019-02-07
申请号：US15667787
申请日：2017-08-03
Applicant: General Electric Company
Inventor： Emily Rosette Clark , Weston Nolan Dooley , Kirk D. Gallier
Abstract: An apparatus and method for cooling an engine component such as an airfoil can include an outer wall separating a cooling fluid flow from a hot flow. A cooling circuit can be provided in the engine component including a cooling passage having at least one pin within the cooling passage with a chevron shape and a non-uniform configuration.
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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
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.
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公开(公告)号：US20170107827A1
公开(公告)日：2017-04-20
申请号：US14884088
申请日：2015-10-15
Applicant: General Electric Company
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/186 , F05D2220/323 , F05D2240/303 , F05D2250/71 , F05D2260/201 , F05D2260/202 , F05D2260/221 , Y02T50/676
Abstract: An airfoil for a gas turbine engine can receive a flow of cooling fluid through a cooling circuit. The cooling circuit is defined within the airfoil comprising a supply passage and a leading edge cooling passage, the two passages being in fluid communication through a plurality of impingement orifices disposed within a cross-over rib disposed between and at least partially defining the passages. The cross-over rib can further comprise a cross-section to provide thermal stress-relief for the cross-over rib.
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