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公开(公告)号：US10267161B2
公开(公告)日：2019-04-23
申请号：US14960924
申请日：2015-12-07
Applicant: General Electric Company
Inventor： Jared Peter Buhler , Ronald Scott Bunker , Victor Hugo Silva Correia , Brian Kenneth Corsetti
IPC: F01D5/18
Abstract: An airfoil for a gas turbine engine can have an exterior wall and an interior wall, with each wall having a thickness. The walls can intersect to define a corner at the intersection. A cooling passage can be defined by the walls at or near the corner to provide fluid communication between the interior and exterior of the airfoil. A film hole can be disposed in the walls and can have a length and diameter to define a ratio of length to diameter, L/D. An arcuate fillet can be located in the corner to define an effective radius for the fillet. The effective radius can be at least 1.5 times larger than the thicknesses of the walls to provide for an increased length to diameter ratio for the film hole.
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公开(公告)号：US10227876B2
公开(公告)日：2019-03-12
申请号：US14960991
申请日：2015-12-07
Applicant: General Electric Company
Inventor： Jared Peter Buhler , Ronald Scott Bunker , Victor Hugo Silva Correia , Brian Kenneth Corsetti
Abstract: A blade for a gas turbine engine comprises an airfoil having a pressure side and a suction side, with a root and a tip wall. The pressure side and suction side extend beyond the tip wall to define a tip channel, defining a plurality of internal and external corners. The corners comprise fillets to define a thickness being greater than the thickness for the pressure, suction, or tip walls. A film hole can extend through the fillet, such that the length of the film hole at the fillet can be increased to define an increased length-to-diameter ratio for the film hole to improve film cooling through the film hole.
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公开(公告)号：US09518474B2
公开(公告)日：2016-12-13
申请号：US14220434
申请日：2014-03-20
Applicant: General Electric Company
Inventor： Jason David Shapiro , Jared Peter Buhler , Brian Kenneth Corsetti
CPC classification number: F01D11/08 , F01D9/04 , F01D11/18 , F01D25/246 , F05D2300/603
Abstract: A composite annular shroud supported by a support assembly including at least one ring and at least partially disposed within the ring. The shroud is biased against and in sealing engagement with an inner flange of the ring. A three ring assembly includes the inner ring disposed radially inwardly of a middle ring disposed radially inwardly of an outer ring and the shroud at least partially disposed within the inner ring. At least three clocking pins extend radially inwardly from the middle ring through slots in the inner ring into notches in the shroud. The middle ring may be an aft end of a support ring fixedly connected to an engine backbone. Mounting pins may be press fitted into pin holes in the middle ring and extend radially outwardly from the middle ring through radial holes in the outer ring.
Abstract translation: 由支撑组件支撑的复合环形护罩，所述支撑组件包括至少一个环并且至少部分地设置在所述环内。 护罩偏压抵靠环的内凸缘并与其密封接合。 三环组件包括设置在外环的径向向内设置的中环的径向向内的内环，并且护罩至少部分地设置在内环内。 至少三个定时销从中间环径向向内延伸穿过内圈中的槽，使其处于护罩中的凹口。 中间环可以是固定地连接到发动机主干的支撑环的后端。 安装销可以压配合到中间环的销孔中，并从中间环径向向外延伸穿过外环的径向孔。
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公开(公告)号：US12188374B2
公开(公告)日：2025-01-07
申请号：US17960230
申请日：2022-10-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Brian Kenneth Corsetti , John Curtis Calhoun , Dane Michael Dale
IPC: F01D5/18
Abstract: An apparatus for an engine component in a turbine engine. The engine component including a wall with a cooling hole having a passage extending between an inlet fluidly coupled to a cooling fluid flow and an outlet at a heated surface. The cooling hole including a layup surface defining a first angle (α) and a layback surface defining a second angle (β).
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公开(公告)号：US20240401483A1
公开(公告)日：2024-12-05
申请号：US18326684
申请日：2023-05-31
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Kirk Douglas Gallier , Zachary Daniel Webster , Brian Kenneth Corsetti
IPC: F01D5/18
Abstract: An airfoil assembly for a turbine engine which generates a hot fluid flow and provides a cooling fluid flow. The airfoil assembly includes a platform with radially spaced upper and lower walls, the platform extending between a platform leading edge and a platform trailing edge to define an axial direction and extending between a pair of slash faces, an airfoil having an airfoil wall extending radially between a root and a tip to define a span length, the platform wall extending from the airfoil wall proximate the root. A fillet extends between the heated surface and the airfoil wall and defines at least a portion of the root. The airfoil assembly further includes a set of film holes.
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Patent Agency Ranking
公开(公告)号：US20180216467A1
公开(公告)日：2018-08-02
申请号：US15422597
申请日：2017-02-02
Applicant: General Electric Company
IPC: F01D5/08 , F01D25/12 , F01D9/02 , F01D11/02 , F04D19/02 , F04D29/08 , F04D29/32 , F04D29/58 , F02K3/06
CPC classification number: F04D29/582 , F01D11/001 , F01D11/02 , F04D29/083 , F04D29/322 , F05D2250/22 , F05D2250/231 , F05D2250/232 , F05D2250/291 , F05D2250/294 , Y02T50/671
Abstract: A turbine engine, such as a gas turbine engine for an aircraft, can include a compressor section, a combustion section, and a turbine section in axial arrangement. The compressor and turbine sections can include a rotating disk having a plurality of blades and a stationary band having a plurality of stationary vanes. The disk and band are spaced axially defining a buffer cavity. One or more extensions extend into the buffer cavity to prevent ingestion of heated gas into the buffer cavity. Recesses on the underside of the extensions can improve the heat transfer coefficient for the extensions.
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公开(公告)号：US20240117743A1
公开(公告)日：2024-04-11
申请号：US17960230
申请日：2022-10-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Brian Kenneth Corsetti , John Curtis Calhoun , Dane Michael Dale
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2240/307 , F05D2250/14 , F05D2250/38 , F05D2260/2214
Abstract: An apparatus for an engine component in a turbine engine. The engine component including a wall with a cooling hole having a passage extending between an inlet fluidly coupled to a cooling fluid flow and an outlet at a heated surface. The cooling hole including a layup surface defining a first angle (α) and a layback surface defining a second angle (β).
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公开(公告)号：US10436038B2
公开(公告)日：2019-10-08
申请号：US15162687
申请日：2016-05-24
Applicant: General Electric Company
Inventor： Jared Peter Buhler , Ronald Scott Bunker , Victor Hugo Silva Correia , Brian Kenneth Corsetti
Abstract: An airfoil for a gas turbine engine includes a pressure side and a suction side, with a root and a tip wall. The pressure side and suction side extend beyond the tip wall to define a tip channel, defining a plurality of internal and external corners. A tip shelf can be defined in the pressure or suction sidewalls. A film hole can extend to the tip shelf, such that the film hole can be shaped to direct a flow of cooling fluid to the film hole to improve film cooling at the tip shelf.
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公开(公告)号：US20190145265A1
公开(公告)日：2019-05-16
申请号：US16247711
申请日：2019-01-15
Applicant: General Electric Company
Inventor： Jared Peter Buhler , Ronald Scott Bunker , Victor Hugo Silva Correia , Brian Kenneth Corsetti
Abstract: A blade for a gas turbine engine comprises an airfoil having a pressure side and a suction side, with a root and a tip wall. The pressure side and suction side extend beyond the tip wall to define a tip channel, defining a plurality of internal and external corners. The corners comprise fillets to define a thickness being greater than the thickness for the pressure, suction, or tip walls. A film hole can extend through the fillet, such that the length of the film hole at the fillet can be increased to define an increased length-to-diameter ratio for the film hole to improve film cooling through the film hole.
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公开(公告)号：US20170159449A1
公开(公告)日：2017-06-08
申请号：US14960924
申请日：2015-12-07
Applicant: General Electric Company
Inventor： Jared Peter Buhler , Ronald Scott Bunker , Victor Hugo Silva Correia , Brian Kenneth Corsetti
IPC: F01D5/18
CPC classification number: F01D5/186 , F01D5/188 , F05D2260/202 , Y02T50/676
Abstract: An airfoil for a gas turbine engine can have an exterior wall and an interior wall, with each wall having a thickness. The walls can intersect to define a corner at the intersection. A cooling passage can be defined by the walls at or near the corner to provide fluid communication between the interior and exterior of the airfoil. A film hole can be disposed in the walls and can have a length and diameter to define a ratio of length to diameter, L/D. An arcuate fillet can be located in the corner to define an effective radius for the fillet. The effective radius can be at least 1.5 times larger than the thicknesses of the walls to provide for an increased length to diameter ratio for the film hole.
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