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公开(公告)号：US20190195073A1
公开(公告)日：2019-06-27
申请号：US15850842
申请日：2017-12-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Viswanadha Gupta Sakala , Douglas Duane Ward , Ming Xie
CPC classification number: F01D5/147 , B29C70/345 , B29C70/38 , B29C70/70 , B29D99/0028 , B29L2031/08 , F01D5/282 , F05D2240/301 , F05D2250/28 , F05D2250/291 , F05D2300/603
Abstract: Composite hollow blade and an associated method of forming the composite hollow blade are disclosed. The method includes forming a core by fabricating a grid core structure based on a plurality of design parameters, where the grid core includes a plurality of first reinforcing components disposed in a first curable matrix material. The method further includes forming an outer layer including a plurality of second reinforcing components disposed in a second curable matrix material. Further, the method includes coupling the core to the outer layer and curing the core and the outer layer to form the composite hollow blade.
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公开(公告)号：US20180283397A1
公开(公告)日：2018-10-04
申请号：US15478702
申请日：2017-04-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Viswanadha Gupta Sakala , Mitchell Harold Boyer , Ming Xie , Douglas Duane Ward
CPC classification number: F04D29/522 , F01D9/02 , F01D21/045 , F02K3/06 , F04D29/542 , F05D2220/32 , F05D2230/10 , F05D2300/10 , F05D2300/603
Abstract: A containment assembly for use in a turbine engine includes a fan case formed from a composite material. The fan case includes a forward end, an aft end, and an opening defined through the fan case between the forward and aft ends. The containment assembly further includes a structural attachment member formed from a metallic material and coupled to the fan case. The structural attachment member is positioned within the opening in the fan case and is configured to receive at least one fastener to couple a component to the structural attachment member.
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公开(公告)号：US20170348876A1
公开(公告)日：2017-12-07
申请号：US15169403
申请日：2016-05-31
Applicant: General Electric Company
Inventor： Wendy Wen-Ling Lin , Douglas Duane Ward , James Dale Steibel
IPC: B29B15/12 , B29C70/54 , B29D99/00 , B32B5/26 , B32B37/00 , B29C35/02 , B29C70/30 , B29L31/30 , B29L31/08 , B29K309/08 , B29K309/02 , B29K305/02 , B29K83/00 , B29K81/00 , B29K79/00
CPC classification number: B29B15/127 , B29C35/02 , B29C70/30 , B29C70/54 , B29D99/0025 , B29K2079/085 , B29K2081/00 , B29K2083/00 , B29K2279/08 , B29K2305/02 , B29K2309/02 , B29K2309/08 , B29L2031/08 , B29L2031/3076 , B32B5/02 , B32B5/12 , B32B5/22 , B32B5/24 , B32B5/26 , B32B18/00 , B32B27/00 , B32B27/12 , B32B27/281 , B32B27/283 , B32B27/286 , B32B27/42 , B32B37/0038 , B32B2250/05 , B32B2250/20 , B32B2260/00 , B32B2260/021 , B32B2260/023 , B32B2260/04 , B32B2260/046 , B32B2262/02 , B32B2262/10 , B32B2262/101 , B32B2262/105 , B32B2311/24 , B32B2315/02 , B32B2315/08 , B32B2379/08 , B32B2603/00 , B32B2605/18 , C04B35/117 , C04B35/565 , C04B35/573 , C04B35/62863 , C04B35/62868 , C04B35/6303 , C04B35/63444 , C04B35/63488 , C04B35/76 , C04B35/803 , C04B35/806 , C04B35/82 , C04B2235/3217 , C04B2235/3826 , C04B2235/422 , C04B2235/428 , C04B2235/483 , C04B2235/5224 , C04B2235/5232 , C04B2235/5244 , C04B2235/616 , C04B2237/38 , F01D5/282 , F01D5/284 , F05D2300/6033 , F05D2300/6034 , Y02T50/672 , Y02T50/673
Abstract: A method of fabricating a laminar composite article, includes steps of spreading a plurality of continuous fiber tows from a spool to form a first ply layer having a substantially consistent layer thickness, applying a binder to the spread plurality of continuous fiber tows, curing the plurality of continuous fiber tows and applied binder at a cure temperature less than a thermal decomposition temperature of the binder, and processing the cured plurality of continuous fiber tows at a post-cure temperature greater than the cure temperature.
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Patent Agency Ranking
公开(公告)号：US20210221491A1
公开(公告)日：2021-07-22
申请号：US17071114
申请日：2020-10-15
Applicant: General Electric Company
Abstract: In an aspect of the present disclosure, an aircraft defining a longitudinal direction and a lateral direction is provided. The aircraft includes: a fuselage; a single unducted rotor engine mounted at a location spaced from the fuselage of the aircraft, the single unducted rotor engine comprising an unducted rotor assembly having a single stage of rotor blades; and a fuselage shield attached to or formed integrally with the fuselage at a location in alignment with the single stage of rotor blades of the unducted rotor assembly along the lateral direction.
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15.发明授权公开(公告)号：US10697470B2
公开(公告)日：2020-06-30
申请号：US15043881
申请日：2016-02-15
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Douglas Duane Ward
Abstract: A containment case includes a fan assembly including a hub having a plurality of fan blades extending radially outward between radially inward blade roots and radially outward blade tips. Containment case includes a radially outer shell circumscribing fan assembly and having a first radially inner surface and a radially outer surface, an inner structure having a second radially inner surface extending along first radially inner surface, and a trench extending circumferentially along second radially inner surface into inner structure from second radially inner surface. The trench is approximately axially aligned with the fan assembly. The containment case also includes, within the trench, a trench filler layer configured to dissipate impact energy from a released fan blade and having a plurality of sheets including a fibrous composite material having a plurality of fibers fabricated within each sheet, where the sheets are coupled together into a repeating pattern of hollow units.
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公开(公告)号：US20190242399A1
公开(公告)日：2019-08-08
申请号：US15891423
申请日：2018-02-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Gregory Carl Gemeinhardt , Douglas Duane Ward , David William Crall , Wendy Wen-Ling Lin
CPC classification number: F04D29/388 , F01D5/147 , F01D21/045 , F04D29/023 , F04D29/325
Abstract: A blade for a turbine engine comprising a composite core defining a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction. The composite core is formed from two materials with different compositions.
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公开(公告)号：US20190242260A1
公开(公告)日：2019-08-08
申请号：US15891415
申请日：2018-02-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Gregory Carl Gemeinhardt , Douglas Duane Ward , David William Crall
Abstract: A blade for the fan section of a turbine engine comprising a composite core defining a pressure side and a suction side extending axially between a core leading edge and a core trailing edge defining a chord-wise direction and extending radially between a core root and a core tip defining a span-wise direction and a leading edge strip mounted to the core leading edge.
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18.发明申请公开(公告)号：US20170234329A1
公开(公告)日：2017-08-17
申请号：US15043881
申请日：2016-02-15
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Douglas Duane Ward
Abstract: A containment case includes a fan assembly including a hub having a plurality of fan blades extending radially outward between radially inward blade roots and radially outward blade tips. Containment case includes a radially outer shell circumscribing fan assembly and having a first radially inner surface and a radially outer surface, an inner structure having a second radially inner surface extending along first radially inner surface, and a trench extending circumferentially along second radially inner surface into inner structure from second radially inner surface. The trench is approximately axially aligned with the fan assembly. The containment case also includes, within the trench, a trench filler layer configured to dissipate impact energy from a released fan blade and having a plurality of sheets including a fibrous composite material having a plurality of fibers fabricated within each sheet, where the sheets are coupled together into a repeating pattern of hollow units.
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