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公开(公告)号：US20140161621A1
公开(公告)日：2014-06-12
申请号：US13709651
申请日：2012-12-10
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Scott Roger Finn , Peggy Lynn Baehmann , Joel Primmer White
IPC: F01D5/14
CPC classification number: F01D5/147 , B29C70/202 , B29C70/38 , B29D99/0025 , B29L2031/082 , F01D5/282 , Y02T50/672
Abstract: A composite article including composite component mounted on a spar including a shank extending heightwise from below component base up into composite component. Tab at an upper end of shank substantially or fully embedded in the composite component and at least one ply surface pattern of the composite component contacting and generally conforming to at least one spar surface pattern on the tab.Spar surface pattern may include spaced apart spar surface protrusions with spar surface spaces therebetween and spar surface protrusions extending outwardly from spar and disposed between tows in ply surface pattern. Tows may be layed up in spar surface spaces. Spar surface pattern may include continuous or segmented spaced spar surface protrusions and spar surface spaces therebetween with tows in ply surface pattern disposed in spar surface spaces. The composite article may be a composite blade or vane including a composite airfoil.
Abstract translation: 一种复合制品，其包括安装在翼梁上的复合部件，该翼梁包括从下部部件基部向上高度延伸的复合部件。 基部或完全嵌入复合部件中的柄的上端处的突片，并且复合部件的至少一个帘布层表面图案接触并且基本上符合突片上的至少一个翼梁表面图案。 翼梁表面图案可以包括间隔开的翼梁表面突起，其间具有翼梁表面空间，并且翼梁表面突起从翼梁向外延伸并且布置在帘布层表面图案中的丝束之间。 拖车可以铺设在翼梁表面空间中。 翼梁表面图案可以包括连续的或分段间隔的翼梁表面突起和其间的翼梁表面空间，其间具有布置在翼梁表面空间中的帘布层表面图案中的丝束。 复合制品可以是包括复合翼型件的复合叶片或叶片。
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公开(公告)号：US20250059894A1
公开(公告)日：2025-02-20
申请号：US18476474
申请日：2023-09-28
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Abhijeet Jayshingrao Yadav , Frank Worthoff , Nicholas Joseph Kray , Nitesh Jain , Balaraju Suresh
Abstract: A turbine engine including a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement. The turbine engine further including a composite airfoil assembly. The composite airfoil assembly having an outer wall, a composite body at least partially defining the outer wall, and a tip cap at least partially defining the outer wall.
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公开(公告)号：US20250052162A1
公开(公告)日：2025-02-13
申请号：US18447525
申请日：2023-08-10
Applicant: GENERAL ELECTRIC COMPANY
Abstract: A gas turbine engine includes a fan section, a compressor section, combustion section, and turbine section in serial flow arrangement, that defining an engine centerline extending between a forward direction and an aft direction. A composite component, such as an airfoil, extends between a root and a tip, defining a span-wise direction therebetween, and between a leading edge and a trailing edge, defining a chord-wise direction therebetween. The composite component includes a preform core including a first set of fibers as a first set of warp fibers and a first set of weft fibers.
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公开(公告)号：US12196107B2
公开(公告)日：2025-01-14
申请号：US18172723
申请日：2023-02-22
Applicant: GENERAL ELECTRIC COMPANY
IPC: F01D5/28
Abstract: A turbine engine comprising a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. The turbine engine includes an airfoil with an outer wall having a pressure side and a suction side, extending between a root and a tip in a span-wise direction, and extending between a leading edge and a trailing edge in a chord-wise direction. The airfoil includes a woven core, a first bonding layer including a toughened region, and a laminate skin provided exterior of the first bonding layer and bonded to the woven core by the first bonding layer.
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公开(公告)号：US20240392801A1
公开(公告)日：2024-11-28
申请号：US18792952
申请日：2024-08-02
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Arthur William Sibbach
IPC: F04D29/32
Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.
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Patent Agency Ranking
公开(公告)号：US20240369071A1
公开(公告)日：2024-11-07
申请号：US18777644
申请日：2024-07-19
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Arthur William Sibbach
Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.
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公开(公告)号：US20240360768A1
公开(公告)日：2024-10-31
申请号：US18764770
申请日：2024-07-05
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Arthur William Sibbach
CPC classification number: F01D5/282 , F01D9/02 , F01D25/005 , F05D2220/323 , F05D2240/12 , F05D2240/30 , F05D2300/603
Abstract: A turbine engine includes a fan and a turbomachine defining an engine centerline. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbine engine also includes a set of composite airfoils circumferentially arranged about the engine centerline. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion. The leading edge protector includes at least one projection extended past a base of the airfoil to a root of the airfoil.
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公开(公告)号：US12110805B2
公开(公告)日：2024-10-08
申请号：US18329467
申请日：2023-06-05
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Viswanadha Gupta Sakala , Nicholas Joseph Kray , Ambika Shivamurthy , Kirti Arvind Petkar
CPC classification number: F01D5/147 , F01D5/02 , G06F30/17 , F05D2220/32 , F05D2230/80 , F05D2240/24
Abstract: Methods, apparatus, systems and articles of manufacture corresponding to a fan blade with intrinsic damping characteristics are disclosed. An example fan blade comprises an exterior body including a first side and a second side; a first hairpin structure in contact with (a) the first side of the exterior body and (b) the second side of the exterior body; and a second hairpin structure in contact with (a) the first side and (b) the second side, wherein the first hairpin structure corresponds to a first stiffness and the second hairpin structure corresponds to a second stiffness different than the first stiffness.
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公开(公告)号：US12103702B2
公开(公告)日：2024-10-01
申请号：US17071308
申请日：2020-10-15
Applicant: General Electric Company
CPC classification number: B64D45/00 , B32B7/022 , B64C1/38 , B32B2307/558 , B32B2307/72 , B32B2307/732 , B32B2571/02 , B32B2605/18
Abstract: An aircraft defining a longitudinal direction and a lateral direction is provided. The aircraft includes a fuselage; an engine mounted at a location spaced from the fuselage of the aircraft, the engine comprising rotor blades; and at least one fuselage shield removably coupled to the fuselage at a location in alignment with the rotor blades along the lateral direction.
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公开(公告)号：US20240288003A1
公开(公告)日：2024-08-29
申请号：US18656078
申请日：2024-05-06
Applicant: General Electric Company
Inventor： Jixian Yao , Trevor Howard Wood , Kishore Ramakrishnan , William Joseph Solomon , Giridhar Jothiprasad , Nicholas Joseph Kray
CPC classification number: F04D29/384 , F04D19/002
Abstract: A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan blades include a first fan blade having a fan blade airfoil body and a metal edge. The fan blade airfoil body has a leading edge. The metal edge is located at the leading edge and has a plurality of fail-fuse elements. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.
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