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公开(公告)号：US20240401482A1
公开(公告)日：2024-12-05
申请号：US18327172
申请日：2023-06-01
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph KRAY , Tod Winton DAVIS , Gary Willard BRYANT, JR.
IPC: F01D5/14
Abstract: A composite airfoil assembly for a gas turbine engine. The composite airfoil assembly includes a composite airfoil having opposite pressure and suction sides and opposite leading and trailing edges. The pressure side and the suction side extend axially between the leading edge and the trailing edge. The composite airfoil has a laminate skin that is applied to at least a portion of a core. A first cladding and a second cladding, having adjacent segments, are located on the pressure side or the suction side of the composite airfoil.
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Patent Agency Ranking
12.发明申请公开(公告)号：US20180202293A1
公开(公告)日：2018-07-19
申请号：US15405656
申请日：2017-01-13
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Narendra Digamber JOSHI , Nicholas Joseph KRAY , Amber Marie ANDREACO , Samar Jyoti KALITA , Paul MARSLAND , Wayne SPENCE
CPC classification number: F01D5/147 , B22F3/1055 , B22F5/04 , B22F2207/01 , B22F2207/11 , B22F2998/10 , B22F2999/00 , B23K26/082 , B23K26/342 , B23K2101/001 , B23K2103/26 , B33Y10/00 , B33Y80/00 , F01D9/041 , F01D25/005 , F05D2220/32 , F05D2300/606 , F05D2300/608
Abstract: The present disclosure generally relates to turbine engine components having multiple controlled metallic grain orientations. In general, the primary grain orientation is aligned substantially perpendicular to the longitudinal axis of the turbine engine component while the secondary grain orientation is aligned substantially parallel to the longitudinal axis. Such controlled grain orientations provide the blades and vanes with increased strength to withstand the thermal-mechanical stresses of the turbine operation. The disclosure also relates to turbines having these fortified components, and methods of manufacturing the components.
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公开(公告)号：US20170370376A1
公开(公告)日：2017-12-28
申请号：US15540653
申请日：2015-12-15
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph KRAY , Kishore BUDUMURU , Jain NITESH , Michael Harvey SCHNEIDER
CPC classification number: F04D29/388 , F01D5/142 , F01D5/147 , F01D5/284 , F01D5/288 , F01D21/04 , F01D21/045 , F04D29/023 , F04D29/325 , Y02T50/672 , Y02T50/673
Abstract: An airfoil material loss control structure is provided. This structure includes at least one fuse zone that, during impact from a foreign object, fail before the surrounding structure. In a further aspect, a rotary machine is provided. This rotary machine includes a ducted fan gas turbine engine including a composite airfoil with at least one fuse zone.
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公开(公告)号：US20170074277A1
公开(公告)日：2017-03-16
申请号：US15308968
申请日：2015-05-06
Applicant: General Electric Company
Inventor： Nicholas Joseph KRAY , Suresh SUBRAMANIAN , Phani NANDULA , Dong-Jin SHIM , Todd Alan ANDERSON , Mark Ernest VERMILYEA
Abstract: According to present embodiments or aspects thereof, a composite booster spool with separable composite blades is provided. The blades are inserted radially from within the inner circumference of the spool and extend outwardly through the spool. The system provides a reduced weight assembly as compared to prior art metallic or composite/metallic combination systems. Additionally, the blades are separable which results in a more field-serviceable assembly over a fully integral system wherein the blades and spool are integrally formed from composites or combination of metal and composites.
Abstract translation: 根据本发明的实施例，提供了一种具有可分离复合叶片的复合助力卷轴。 叶片从卷轴的内周径向插入并且通过卷轴向外延伸。 与现有技术的金属或复合/金属组合系统相比，该系统提供了减重组件。 此外，叶片是可分离的，其导致在完全整体系统上的更多的现场维修组件，其中叶片和卷轴由复合材料或金属和复合材料的组合一体形成。
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公开(公告)号：US20160341052A1
公开(公告)日：2016-11-24
申请号：US14893639
申请日：2014-05-29
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Qiang LI , Nicholas Joseph KRAY , Scott Roger FINN
CPC classification number: F01D5/3092 , F01D5/282 , F01D5/284 , F01D5/3007 , F01D5/3084 , F04D29/324 , F05D2220/36 , F05D2240/30 , F05D2260/941 , F05D2300/174 , F05D2300/6033 , Y02T50/672
Abstract: A composite airfoil comprises a leading edge and a trailing edge, a pressure side and a suction side extending between the leading edge and the trailing edge, a tip at a radial outer end of the airfoil, a shank at a radial inner end of the airfoil, a dovetail connected to the shank, and a metal patch disposed between the dovetail and the shank.
Abstract translation: 复合翼型件包括前缘和后缘，压力侧和在前缘和后缘之间延伸的吸力侧，在翼型件的径向外端处的尖端，在翼型件的径向内端处的柄部 ，连接到柄的燕尾榫和设置在燕尾榫和柄之间的金属补片。
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公开(公告)号：US20160333889A1
公开(公告)日：2016-11-17
申请号：US15111199
申请日：2014-11-17
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph KRAY , Qiang LI
CPC classification number: F04D29/34 , F01D5/282 , F01D5/288 , F01D5/3007 , F01D5/3092 , F04D29/023 , F04D29/325 , Y02T50/672
Abstract: A gas turbine engine blade root shim for use between a composite blade root and a wall of a slot in a rotor includes a longitudinally extending base having distal first and second transversely spaced apart ends, first and second longitudinally extending legs acutely angled inwardly towards the base from the first and second ends, and one or more apertures disposed through each of the longitudinally extending first and second legs. Apertures may include rectangular slots having rounded edges along the first and second outwardly facing surfaces of the first and second legs respectively and/or rounded corners between the first and second outwardly facing surfaces and the first and second inwardly facing surfaces of the first and second legs. Low coefficient of friction coatings may be disposed on outwardly facing surfaces, of the legs. Coatings may include polytetrafluoroethylene powder dispersed in a resin binder and other coatings having polytetrafluoroethylene.
Abstract translation: 用于在复合叶片根部和转子中的槽的壁之间使用的燃气涡轮发动机叶片根垫片包括纵向延伸的基部，其具有远端第一和第二横向间隔开的端部，第一和第二纵向延伸的腿向内朝向基部 从第一端和第二端以及穿过每个纵向延伸的第一和第二腿设置的一个或多个孔。 孔可以包括具有沿着第一和第二腿的第一和第二向外表面的圆形边缘的矩形槽和/或第一和第二向外表面之间的圆角以及第一和第二腿的第一和第二向内的表面 。 低摩擦系数涂层可以设置在腿的向外的表面上。 涂层可以包括分散在树脂粘合剂中的聚四氟乙烯粉末和具有聚四氟乙烯的其它涂层。
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