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公开(公告)号：US20220372884A1
公开(公告)日：2022-11-24
申请号：US17328706
申请日：2021-05-24
Inventor： Nicholas J. Kray , Nicholas M. Daggett , Frank Worthoff , Damian Osowski
IPC: F01D5/32
Abstract: Preload sleeves and/or other retainers for a collet-mounted blade dovetail and/or other root are disclosed. An example turbofan for an engine includes a trunnion forming a socket for a root of a blade, a primary collet positioning the root with respect to the trunnion, and a radial preload retainer at least partially encircling the primary collet and applying a radial force with respect to the primary collet to support the primary collet positioning the root with respect to the trunnion.
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公开(公告)号：US11913346B2
公开(公告)日：2024-02-27
申请号：US16891665
申请日：2020-06-03
Applicant: General Electric Company
Inventor： Frank Worthoff , Benjamin James Roby , Scott Roger Finn
CPC classification number: F01D21/045 , B32B5/12 , B32B5/263 , F04D29/023 , F04D29/526 , B32B2260/023 , B32B2262/101 , B32B2262/106 , B32B2307/558 , B32B2605/18 , F05D2220/36 , F05D2230/50 , F05D2240/14 , F05D2300/2102 , F05D2300/603 , F05D2300/6012
Abstract: An apparatus a multiple layer structure having a sub-portion defining an impact zone, and having an inner composite fiber layer, an outer composite fiber layer overlying the inner composite fiber layer, and a woven glass layer, where the inner composite fiber layer, outer composite fiber layer, and the woven glass layer overly the impact zone.
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公开(公告)号：US20250075672A1
公开(公告)日：2025-03-06
申请号：US18430811
申请日：2024-02-02
Applicant: General Electric Company , GE Aviation Systems Limited
Inventor： Nicholas M. Daggett , Frank Worthoff , Pawel Pres , Daryl John Burford
Abstract: A trunnion-to-disk connection for use on an open fan configuration of a gas turbine engine may include an integral trunnion and blade spar inserted through a trunnion aperture of a fan disk and supported by top bearing and a bottom bearing. A cavity can be provided between a trunnion of the integral trunnion and blade spar and the fan disk, as well as between the top bearing and bottom bearing. Pressurized hydraulic fluid can be supplied to the cavity to urge the integral trunnion and blade spar in a direction to preload the bearings. Prior to pressurization, and prior to installation of the bottom bearing, the trunnion can be inserted into a trunnion aperture of the fan disk such that an end of the trunnion extends past the fan disk to provide sufficient space to insert the bottom bearing from within the open interior of the fan disk.
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公开(公告)号：US12012898B2
公开(公告)日：2024-06-18
申请号：US17979992
申请日：2022-11-03
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Egbert Geertsema , Arthur W. Sibbach , Andrew Hudecki , Timothy Richard DePuy , John C. Schilling , Frank Worthoff , Tsuguji Nakano
CPC classification number: F02C7/24 , F02C7/36 , F05D2260/96
Abstract: A gas turbine engine comprises a fan, a core turbine engine coupled to the fan, a fan case housing the fan and the core turbine engine, a plurality of outlet guide vanes extending between the core turbine engine and the fan case, and an acoustic spacing. The fan comprises a plurality of fan blades that define a fan diameter and a BEAL. The fan case comprises an inlet and an inlet length between the inlet and the fan. The acoustic spacing comprises a distance between the fan and the plurality of outlet guide vanes, and in combination with the BEAL determines an acoustic spacing ratio of the gas turbine engine.
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公开(公告)号：US10711635B2
公开(公告)日：2020-07-14
申请号：US15805467
申请日：2017-11-07
Applicant: General Electric Company
Inventor： Frank Worthoff , Benjamin James Roby , Scott Roger Finn
Abstract: An apparatus and method for a multiple layer fan casing surrounding a fan having a plurality of circumferentially spaced blades rotatable about a rotational axis and having a sub-portion defining a blade impact zone, the multiple layers comprising an inner fiber layer confronting the blades, an outer fiber layer overlying the inner carbon layer, a glass layer sandwiched between the inner and outer composite fiber layers.
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Patent Agency Ranking
公开(公告)号：US12292017B1
公开(公告)日：2025-05-06
申请号：US18744069
申请日：2024-06-14
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Egbert Geertsema , Arthur W. Sibbach , Andrew Hudecki , Timothy Richard DePuy , John C. Schilling , Frank Worthoff , Tsuguji Nakano
Abstract: A gas turbine engine comprises a fan, a core turbine engine coupled to the fan, a fan case housing the fan and the core turbine engine, a plurality of outlet guide vanes extending between the core turbine engine and the fan case, and an acoustic spacing. The fan comprises a plurality of fan blades that define a fan diameter and a BEAL. The fan case comprises an inlet and an inlet length between the inlet and the fan. The acoustic spacing comprises a distance between the fan and the plurality of outlet guide vanes, and in combination with the BEAL determines an acoustic spacing ratio of the gas turbine engine.
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公开(公告)号：US20240151185A1
公开(公告)日：2024-05-09
申请号：US17979992
申请日：2022-11-03
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Egbert Geertsema , Arthur W. Sibbach , Andrew Hudecki , Timothy Richard DePuy , John C. Schilling , Frank Worthoff , Tsuguji Nakano
CPC classification number: F02C7/24 , F02C7/36 , F05D2260/96
Abstract: A gas turbine engine comprises a fan, a core turbine engine coupled to the fan, a fan case housing the fan and the core turbine engine, a plurality of outlet guide vanes extending between the core turbine engine and the fan case, and an acoustic spacing. The fan comprises a plurality of fan blades that define a fan diameter and a BEAL. The fan case comprises an inlet and an inlet length between the inlet and the fan. The acoustic spacing comprises a distance between the fan and the plurality of outlet guide vanes, and in combination with the BEAL determines an acoustic spacing ratio of the gas turbine engine.
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公开(公告)号：US11913408B1
公开(公告)日：2024-02-27
申请号：US18301405
申请日：2023-04-17
Applicant: General Electric Company , GE Aviation Systems Limited
Inventor： Nicholas M. Daggett , Frank Worthoff , Pawel Pres , Daryl John Burford
CPC classification number: F02K3/06 , F04D29/34 , F04D29/601
Abstract: A trunnion-to-disk connection for use on an open fan configuration of a gas turbine engine may include an integral trunnion and blade spar inserted through a trunnion aperture of a fan disk and supported by top bearing and a bottom bearing. A cavity can be provided between a trunnion of the integral trunnion and blade spar and the fan disk, as well as between the top bearing and bottom bearing. Pressurized hydraulic fluid can be supplied to the cavity to urge the integral trunnion and blade spar in a direction to preload the bearings. Prior to pressurization, and prior to installation of the bottom bearing, the trunnion can be inserted into a trunnion aperture of the fan disk such that an end of the trunnion extends past the fan disk to provide sufficient space to insert the bottom bearing from within the open interior of the fan disk.
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公开(公告)号：US09421744B2
公开(公告)日：2016-08-23
申请号：US14479871
申请日：2014-09-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sultan Shair , Julian Thomas O'Flynn , Mathias Ernst Messmer , Frank Worthoff , Mile Ostojic , Mark Ernest Vermilyea
IPC: B29C65/48 , B29C65/52 , B32B37/12 , B32B37/26 , B32B38/10 , B32B43/00 , B32B37/00 , B29C70/38 , B29C65/78 , B32B37/02 , B32B37/14 , B32B38/00 , B29C33/68 , B29C65/18 , B29C65/20 , B29C65/00 , B32B38/18 , B65H41/00
CPC classification number: B32B37/0007 , B29C33/68 , B29C65/18 , B29C65/20 , B29C65/78 , B29C66/004 , B29C66/80 , B29C66/83413 , B29C70/38 , B32B37/0053 , B32B37/02 , B32B37/144 , B32B37/146 , B32B37/26 , B32B38/0036 , B32B38/1858 , B32B2037/262 , B32B2305/022 , B32B2305/024 , B32B2305/77 , B32B2309/12 , B65H41/00 , Y10T156/16 , Y10T156/17 , Y10T156/1994
Abstract: A method for applying at least one ply onto a tool or an uncured composite layup disposed on the tool includes automatically controlling slidably removing at least one nonstick separator relative to the at least one ply positioned on the at least one nonstick separator to inhibit at least a portion of the at least one ply from adhering to the tool or uncured composite layup while applying a moving compressive force to an outer surface of the at least one ply relative to a moving trailing edge of the at least one nonstick separator to adhere at least a portion of the at least one ply to the tool or to the uncured composite layup.
Abstract translation: 用于将至少一层施加到设置在工具上的工具或未固化的复合叠层上的方法包括自动控制相对于位于至少一个不粘分离器上的至少一层的至少一个不粘分离器滑动地移除，以至少抑制 所述至少一个帘布层的一部分粘附到所述工具或未固化的复合材料叠层上，同时相对于所述至少一个不粘分离器的移动后缘施加移动的压缩力至所述至少一个帘布层的外表面，以将至少一个 所述至少一层的所述部分至所述工具或所述未固化复合材料叠层。
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公开(公告)号：US20140374003A1
公开(公告)日：2014-12-25
申请号：US14479871
申请日：2014-09-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sultan Shair , Julian Thomas O'Flynn , Mathias Ernst Messmer , Frank Worthoff , Mile Ostojic , Mark Ernest Vermilyea
CPC classification number: B32B37/0007 , B29C33/68 , B29C65/18 , B29C65/20 , B29C65/78 , B29C66/004 , B29C66/80 , B29C66/83413 , B29C70/38 , B32B37/0053 , B32B37/02 , B32B37/144 , B32B37/146 , B32B37/26 , B32B38/0036 , B32B38/1858 , B32B2037/262 , B32B2305/022 , B32B2305/024 , B32B2305/77 , B32B2309/12 , B65H41/00 , Y10T156/16 , Y10T156/17 , Y10T156/1994
Abstract: A method for applying at least one ply onto a tool or an uncured composite layup disposed on the tool includes automatically controlling slidably removing at least one nonstick separator relative to the at least one ply positioned on the at least one nonstick separator to inhibit at least a portion of the at least one ply from adhering to the tool or uncured composite layup while applying a moving compressive force to an outer surface of the at least one ply relative to a moving trailing edge of the at least one nonstick separator to adhere at least a portion of the at least one ply to the tool or to the uncured composite layup.
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