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公开(公告)号：US09878501B2
公开(公告)日：2018-01-30
申请号：US14596841
申请日：2015-01-14
Applicant: General Electric Company
Inventor： Darek Tomasz Zatorski , Ian Francis Prentice , Randy M. Vondrell , Andrew Breeze-Stringfellow
CPC classification number: B29C70/34 , B29D99/0025
Abstract: A method of manufacturing a frangible laminate is provided. The method comprises constructing a reinforced polymer matrix, cutting the reinforced polymer matrix into a plurality of laminae, forming a laminate via stacking the plurality of laminae and at least one energy dissipating member, and consolidating the laminate.
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公开(公告)号：US20210215062A1
公开(公告)日：2021-07-15
申请号：US17213503
申请日：2021-03-26
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Ian Francis Prentice , Daniel Alan Niergarth
Abstract: A fan for a gas turbine engine is provided. The fan includes a plurality of fan blades, a disk, and a trunnion mechanism for attaching the fan blades to the disk. The disk can be formed of a plurality of individual disk segments, with the trunnion mechanism attaching one of the plurality of fan blades to a respective disk segment. A retention member is also provided. The retention member includes a means for catching a portion of the trunnion mechanism should a primary attachment system of the trunnion mechanism fail.
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公开(公告)号：US20190093503A1
公开(公告)日：2019-03-28
申请号：US16108133
申请日：2018-08-22
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Ian Francis Prentice , Daniel Alan Niergarth
Abstract: A fan for a gas turbine engine is provided. The fan includes a plurality of fan blades, a disk, and a trunnion mechanism for attaching the fan blades to the disk. The disk can be formed of a plurality of individual disk segments, with the trunnion mechanism attaching one of the plurality of fan blades to a respective disk segment. A retention member is also provided. The retention member includes a means for catching a portion of the trunnion mechanism should a primary attachment system of the trunnion mechanism fail.
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公开(公告)号：US09828862B2
公开(公告)日：2017-11-28
申请号：US14596804
申请日：2015-01-14
Applicant: General Electric Company
Inventor： Darek Tomasz Zatorski , Ian Francis Prentice , Randy M. Vondrell , Andrew Breeze-Stringfellow , Raymond Anthony Humble
CPC classification number: F01D5/282 , F01D5/147 , F01D21/04 , F01D21/045 , F04D29/324 , Y02T50/672
Abstract: A frangible airfoil that mitigates adverse conditions associated with release of material resulting from impact damage to the composite blade is provided, the airfoil having provisions for dissipating energy, self-shredding, and predetermined release trajectory.
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公开(公告)号：US09725155B2
公开(公告)日：2017-08-08
申请号：US14984758
申请日：2015-12-30
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Ian Francis Prentice , Trevor Wayne Goerig , Trevor Howard Wood , Kishore Ramakrishnan , Andrew Breeze-Stringfellow
Abstract: An aircraft and method of operating the aircraft are provided. The aircraft includes a fuselage including a nose, a tail, and a hollow, elongate body extending therebetween, a wing extending laterally away from the fuselage, the wing including a leading edge in a direction of motion of the aircraft during normal flight and a trailing edge on an opposing edge of the wing, and an engine configured to drive a bladed rotatable member, the engine coupled to at least one of the wing and the fuselage. The aircraft further includes at least one of a forward chine member and an aft chine member extending from the fuselage at a point forward of the engine aftward to a point aft of the bladed rotatable member.
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Patent Agency Ranking
公开(公告)号：US20160167798A1
公开(公告)日：2016-06-16
申请号：US14568555
申请日：2014-12-12
Applicant: General Electric Company
Inventor： Ian Francis Prentice
CPC classification number: B64D27/26 , B64C19/00 , B64D27/10 , B64D27/16 , B64D2027/005 , B64D2027/266
Abstract: Aircraft engine mounted to aircraft pylon with variable pitch mounting system includes variable length actuator disposed between engine and pylon for pitching engine relative to pylon. Spaced apart pylon front and rear mounts may pivotably mount front and rear stationary engine components of engine to front and rear mount positions on pylon. Front and rear linkages may vertically suspend engine from pylon with pivotable links disposed between pylon front and rear mounts and front and rear stationary engine components. One or more thrust links may be pivotably joined at link rear ends to pylon rear mount and at link forward ends to front support frame. Alternative mounting system may include support structure cantilevered off pylon for pivotably supporting engine and actuator substantially horizontally disposed between engine and pylon. Incidence angle between engine centerline axis and air streamlines may be adjusted by changing length of actuator.
Abstract translation: 安装在具有可变桨距安装系统的飞机吊架上的飞机发动机包括设置在发动机和塔架之间的可变长度致动器，用于相对于塔架来引导发动机。 分开的塔架前后悬架可以将发动机的前后固定发动机部件可枢转地安装在塔架上的前后安装位置。 前连杆和后连杆可以将引擎垂直悬挂在塔架之间，枢轴连杆设置在塔架前后安装件和前后固定发动机部件之间。 一个或多个推力连杆可以在连杆后端可枢转地连接到塔架后部安装件上，并且在连杆前端可枢转地连接到前支撑框架。 替代安装系统可以包括用于可枢转地支撑发动机和执行器的支撑结构悬臂式离合塔，其基本上水平地设置在发动机和塔架之间。 发动机中心线和空气流线之间的入射角可以通过改变执行器的长度来调节。
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公开(公告)号：US20160032939A1
公开(公告)日：2016-02-04
申请号：US14447984
申请日：2014-07-31
Applicant: General Electric Company
Inventor： Todd Alan Anderson , Wendy Wen-Ling Lin , Pranav Dhoj Shah , Nicholas Joseph Kray , Ian Francis Prentice , Dong-Jin Shim , Xiaomei Fang , Ross Ashely Spoonire
CPC classification number: B29C70/34 , B29C70/24 , B29C70/44 , B29C70/48 , B29L2031/08 , F01D5/282 , F04D29/324 , F05D2220/36 , F05D2300/6034 , Y02T50/672
Abstract: An airfoil structure includes a composite core including a triaxial braid, wherein the triaxial braid includes a longitudinal axis, a first bias fiber extending in a first bias direction at a first bias angle to the longitudinal axis, a second bias fiber extending in a second bias direction at a second bias angle to the longitudinal axis, and an axial fiber extending in a direction parallel to the longitudinal axis. The airfoil structure further includes an outer layer substantially surrounding the composite core, wherein the outer layer includes a plurality of unidirectional prepreg layers.
Abstract translation: 翼型结构包括包括三轴编织物的复合芯，其中所述三轴编织物包括纵向轴线，以与所述纵向轴线成第一偏置角度的第一偏置方向延伸的第一偏置光纤，以第二偏压延伸的第二偏置光纤 方向相对于纵向轴线具有第二偏置角，以及在平行于纵向轴线的方向上延伸的轴向纤维。 翼型结构还包括基本上围绕复合芯的外层，其中外层包括多个单向预浸料层。
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公开(公告)号：US11053812B2
公开(公告)日：2021-07-06
申请号：US16108133
申请日：2018-08-22
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Ian Francis Prentice , Daniel Alan Niergarth
Abstract: A fan for a gas turbine engine is provided. The fan includes a plurality of fan blades, a disk, and a trunnion mechanism for attaching the fan blades to the disk. The disk can be formed of a plurality of individual disk segments, with the trunnion mechanism attaching one of the plurality of fan blades to a respective disk segment. A retention member is also provided. The retention member includes a means for catching a portion of the trunnion mechanism should a primary attachment system of the trunnion mechanism fail.
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公开(公告)号：US10436056B2
公开(公告)日：2019-10-08
申请号：US14747114
申请日：2015-06-23
Applicant: General Electric Company
Inventor： Ian Francis Prentice
Abstract: A feedback sensor system is provided. The feedback sensor system includes a first ring rotatable about an axial direction and a second ring also rotatable about the axial direction. The first ring includes one or more first ring features and the second ring includes one or more second ring features. The feedback sensor system also includes a sensor directed at the surface of the first ring for sensing a parameter influenced by the one or more first ring features and the one or more second ring features. The sensor may determine a position of the first ring relative to the second ring by sensing the parameter.
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公开(公告)号：US10100653B2
公开(公告)日：2018-10-16
申请号：US14878008
申请日：2015-10-08
Applicant: General Electric Company
IPC: F01D5/32 , F01D7/00 , F04D29/32 , F04D29/64 , F01D5/02 , F01D5/12 , F01D5/30 , F02C3/04 , B64C11/32
Abstract: A variable pitch fan for a gas turbine engine includes a fan blade defining a pitch axis and attached at a radially inner end to a trunnion mechanism. The variable pitch fan also includes a disk having a disk segment with the trunnion mechanism extending at least partially through the disk segment. A key is positioned at least partially in a key slot defined in a base of the trunnion mechanism, and further positioned adjacent to a support member of the disk segment. The key defines a first contact line between the key and the key slot and a second contact line between the key and the support member. The first and second contact lines respectively define a first contact reference line in a second contact reference line. The first and second contact reference lines define an angle with the pitch axis of the fan blade greater than zero degrees and less than ninety degrees.
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