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公开(公告)号：US11519284B2
公开(公告)日：2022-12-06
申请号：US16890473
申请日：2020-06-02
Applicant: General Electric Company
Inventor： Matthew Lee Krumanaker , Thomas Joseph Lipinski
Abstract: A turbine engine having an engine core, a first seal structure, a plurality of circumferentially arranged vanes, a plurality of struts, and a second seal structure. The engine core can define a rotor and a stator having a casing. The first seal structure can include a finger seal projecting from the rotor. The plurality of circumferentially arranged vanes can include an uppers band mounted to the casing, and a lower band located radially above the finger seal. At least some of the struts of the plurality of struts can extend through the plurality of circumferentially arranged vanes. The second seal structure can form a seat with the lower band.
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公开(公告)号：US20210372290A1
公开(公告)日：2021-12-02
申请号：US16890473
申请日：2020-06-02
Applicant: General Electric Company
Inventor： Matthew Lee Krumanaker , Thomas Joseph Lipinski
Abstract: A turbine engine comprising an engine core comprising at least a compressor section, a combustor section, and a turbine section and defining a rotor and a stator. The turbine engine further comprising a first seal structure circumferentially extending about the rotor, a plurality of circumferentially arranged vanes, a plurality of struts extending through the vanes, and a second seal structure extending circumferentially about the first seal structure.
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公开(公告)号：US10563518B2
公开(公告)日：2020-02-18
申请号：US15043933
申请日：2016-02-15
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Douglas Gerard Konitzer , Matthew Lee Krumanaker , Weston Nolan Dooley , James Herbert Deines
Abstract: An apparatus and method for an airfoil for a gas turbine engine includes a trailing edge cooling circuit utilizing a plurality of trailing edge ejection holes. The ejection holes can include a circumferentially radiused inlet, a converging section, a metering section, and a diverging section to improve airfoil cooling as well as castability.
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公开(公告)号：US10443398B2
公开(公告)日：2019-10-15
申请号：US14884100
申请日：2015-10-15
Applicant: General Electric Company
Abstract: An airfoil for a gas turbine engine comprises a cooling circuit defined within the airfoil providing a flow of cooling fluid within the airfoil. The cooling circuit exhausts the flow of cooling fluid out a slot opening comprising an airfoil element. The slot opening further defines an acceleration zone and a deceleration zone to meter the flow of cooling fluid within the airfoil.
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公开(公告)号：US20170107828A1
公开(公告)日：2017-04-20
申请号：US14884100
申请日：2015-10-15
Applicant: General Electric Company
Abstract: An airfoil for a gas turbine engine comprises a cooling circuit defined within the airfoil providing a flow of cooling fluid within the airfoil. The cooling circuit exhausts the flow of cooling fluid out a slot opening comprising an airfoil element. The slot opening further defines an acceleration zone and a deceleration zone to meter the flow of cooling fluid within the airfoil.
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Patent Agency Ranking
公开(公告)号：US20170107824A1
公开(公告)日：2017-04-20
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
CPC classification number: F01D5/187 , F01D5/147 , F01D5/18 , F01D9/041 , F01D25/12 , F04D29/324 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2240/303 , F05D2240/305 , F05D2240/306 , F05D2250/185 , F05D2260/201 , F05D2260/202 , Y02T50/676
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：US11021969B2
公开(公告)日：2021-06-01
申请号：US16214411
申请日：2018-12-10
Applicant: General Electric Company
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：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：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：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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