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公开(公告)号：US20170107825A1
公开(公告)日：2017-04-20
申请号：US14884057
申请日：2015-10-15
Applicant: General Electric Company
Inventor： Matthew Lee Krumanaker , Robert Frederick Bergholz , Aaron Ezekiel Smith , Weston Nolan Dooley
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2260/203 , F05D2260/941 , Y02T50/676
Abstract: An engine comprises an airfoil having at least one internal cooling circuit extending radially from the longitudinal axis of the engine. The cooling circuit is defined by at least one rib extending across an interior of the airfoil and at least one internal wall defining an internal passage. The internal wall further defines one or more near wall cooling passages. A thermal stress reduction structure is provided between the rib and the internal wall, providing efficient cooling at a junction between the rib and the internal wall.
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公开(公告)号：US20150159871A1
公开(公告)日：2015-06-11
申请号：US14407076
申请日：2013-06-13
Applicant: General Electric Company
Inventor： Shawn Michael Pearson , Robert Frederick Bergholz , Douglas Ray Smith , Frederick Alan Buck , Stephen Mark Molter , Kevin Robert Feldmann
CPC classification number: F23R3/04 , F01D5/186 , F01D9/023 , F01D9/065 , F02K1/822 , F05D2240/11 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R3/06 , F23R2900/03042 , Y02T50/676
Abstract: A gas turbine engine wall is provided. The wall includes an inner surface and an opposing outer surface having at least one film cooling hole defined therein. The at least one film cooling hole includes an inclined inlet bore that extends from the inner surface and a pair of channels that diverge laterally from an outlet end of the inclined inlet bore. The pair of channels have a substantially constant width and are separated by a ridge to form a boomerang cross-sectional shape.
Abstract translation: 提供燃气涡轮发动机壁。 壁包括内表面和相对的外表面，其中限定有至少一个膜冷却孔。 所述至少一个膜冷却孔包括从内表面延伸的倾斜入口孔和从倾斜入口孔的出口端横向分开的一对通道。 一对通道具有基本上恒定的宽度并且由脊分开以形成回旋形横截面形状。
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Patent Agency Ranking
公开(公告)号：US20220170383A1
公开(公告)日：2022-06-02
申请号：US17673426
申请日：2022-02-16
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Robert Frederick Bergholz , Jason Randolph Allen , Robert David Briggs , Kevin Robert Feldmann , Curtis Walton Stover , Zachary Daniel Webster , Fernando Reiter
IPC: F01D25/12 , F23R3/00 , F01D5/18 , F23R3/06 , F01D9/04 , F01D11/08 , F02C3/04 , F02C7/18 , F23R3/04
Abstract: An engine component assembly with a first substrate having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface, with the cooling surface being different than the hot surface, a second substrate having a first surface in fluid communication with a cooling fluid supply and a second surface, different from the first surface, facing and spaced from the cooling surface to define at least one interior cavity. At least one cavity is provided within the first substrate defining a cavity surface where at least a portion of the cavity surface is directly opposite the second surface. At least one cooling aperture extending through the second substrate from the first surface to the second surface, and defining a streamline along which a cooling fluid passes from the cooling fluid supply to the at least one interior cavity.
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公开(公告)号：US10386069B2
公开(公告)日：2019-08-20
申请号：US14407076
申请日：2013-06-13
Applicant: General Electric Company
Inventor： Shawn Michael Pearson , Robert Frederick Bergholz , Douglas Ray Smith , Frederick Alan Buck , Stephen Mark Molter , Kevin Robert Feldmann
Abstract: A gas turbine engine wall is provided. The wall includes an inner surface and an opposing outer surface having at least one film cooling hole defined therein. The at least one film cooling hole includes an inclined inlet bore that extends from the inner surface and a pair of channels that diverge laterally from an outlet end of the inclined inlet bore. The pair of channels have a substantially constant width and are separated by a ridge to form a boomerang cross-sectional shape.
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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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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
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。
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