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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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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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Patent Agency Ranking
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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公开(公告)号：US20240280024A1
公开(公告)日：2024-08-22
申请号：US18171533
申请日：2023-02-20
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Arthur William Sibbach
CPC classification number: F01D5/147 , F01D5/282 , F05D2220/36 , F05D2240/121 , F05D2240/303 , F05D2300/603
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：US12065943B2
公开(公告)日：2024-08-20
申请号：US17533566
申请日：2021-11-23
Applicant: General Electric Company
Inventor： Li Zheng , Nicholas Joseph Kray , Scott Roger Finn
CPC classification number: F01D5/147 , F01D5/282 , F05D2300/505 , F05D2300/603
Abstract: Morphable rotor blades for a turbine engine systems include a root portion and an airfoil portion having a morphable portion including a morphable material that changes shape in response to a stimulus.
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公开(公告)号：US20240151147A1
公开(公告)日：2024-05-09
申请号：US17979853
申请日：2022-11-03
Applicant: General Electric Company
Inventor： Gary Willard Bryant, Jr. , Nicholas Joseph Kray , Ming Xie , Elzbieta Kryj-Kos , Douglas Lorrimer Armstrong , Nicholas M. Daggett , Frank Worthoff , Scott Roger Finn
IPC: F01D5/28
CPC classification number: F01D5/282 , F05D2220/32 , F05D2230/60 , F05D2300/603
Abstract: The present disclosure relates to an airfoil assembly for a turbine engine and methods of assembly thereof. The airfoil assembly generally includes a composite airfoil and a spar. The composite airfoil has a pressure side and a suction side extending in an axial direction between a leading edge and a trailing edge defining a chordwise direction and extending radially between a root and a tip defining a spanwise direction and having a span-length. The spar includes a first portion including a first material and a second portion joined at an interface with the first portion. The second portion further includes a second material, different from the first material, joined to the first portion at an interface. The method generally includes joining the first portion with the second portion at the interface; and assembling the spar with the composite airfoil.
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