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公开(公告)号：US20240309763A1
公开(公告)日：2024-09-19
申请号：US18182559
申请日：2023-03-13
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F01D5/147 , F01D5/288 , F05D2220/36 , F05D2300/6034
Abstract: A gas turbine engine includes a fan section, a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. Sets of blades can be rotatably driven about the longitudinal axis in the fan section, the compressor section, and the turbine section. The airfoil structure defining one or more of the blades or vanes can include a structure which includes a woven or foam core, with a laminate skin, and an exterior coating.
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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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3.发明申请公开(公告)号：US20170191448A1
公开(公告)日：2017-07-06
申请号：US14984418
申请日：2015-12-30
Applicant: General Electric Company
Inventor： John Joseph Wunsch , Michael John Franks , Danielle Marie Greenfield , Michael Stephens Bodey , Randall Maurice Prather
CPC classification number: F01D25/243 , F01D25/24 , F02K1/78 , F05D2300/121 , F05D2300/603 , F05D2300/702 , Y02T50/672
Abstract: A composite duct panel assembly is provided. The composite duct panel assembly includes a composite duct panel having a curved cross-section in a circumferential direction and a width based on the panel including a portion of a circumference of an annular bypass duct. In one embodiment, at least two adjacent corners of the panel are greater than 90°. In one embodiment, the panel includes a circumferential flange along a circumferential edge and an axial flange along an axial edge, and the assembly further includes a corner bracket coupled to the panel, the circumferential flange, and the axial flange. The corner bracket includes a flange corner having an approximate 90° angle, the flange corner extending the axial flange and the circumferential flange to an intersection at a corner of the panel.
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公开(公告)号：US12286903B2
公开(公告)日：2025-04-29
申请号：US18173989
申请日：2023-02-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Benjamin Thomas Van Oflen , Gary Willard Bryant, Jr. , Michael John Franks , Elzbieta Kryj-Kos , Nicholas Joseph Kray , Arthur William Sibbach
Abstract: A turbine engine having a disk and a composite airfoil assembly. The disk having a slot. The composite airfoil assembly having an airfoil portion, a dovetail portion, and a roll snubber. The dovetail portion having a radially inner surface. The roll snubber being provided on the radially inner surface. The radially inner surface spaced from the slot to define a gap therebetween.
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公开(公告)号：US12241383B2
公开(公告)日：2025-03-04
申请号：US18173952
申请日：2023-02-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Benjamin Thomas Van Oflen , Gary Willard Bryant, Jr. , Nicholas Joseph Kray , Arthur William Sibbach , Michael John Franks , Elzbieta Kryj-Kos
Abstract: A turbine engine having a disk, a composite airfoil assembly and a pitch snubber. The disk having a slot. The composite airfoil assembly having an airfoil portion and a dovetail portion. The dovetail portion having a radially inner surface spaced from the slot to define a gap therebetween. The pitch snubber being provided on one of the slot or the radially inner surface of the dovetail portion.
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Patent Agency Ranking
公开(公告)号：US10465558B2
公开(公告)日：2019-11-05
申请号：US15318121
申请日：2015-04-28
Applicant: General Electric Company
Inventor： Jason David Shapiro , Michael John Franks , David Scott Stapleton
Abstract: A shroud hanger assembly or shroud assembly is provided for components which may be formed of materials having differing coefficient thermal expansion. The assembly includes a multi-piece hanger including a shroud positioned in a cavity between a first hanger portion and a second hanger portion. A shroud may be formed of a low coefficient of thermal expansion material which may have a differing coefficient thermal expansion than the material defining the shroud hanger. The shroud is deflected by an axial force acting between the hanger and the shroud which also forms a seal. The seal compensates for differing rates of thermal growth between the shroud and the hanger throughout the engine operating envelope.
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公开(公告)号：US20250012192A1
公开(公告)日：2025-01-09
申请号：US18348452
申请日：2023-07-07
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Arthur William Sibbach , Nicholas Joseph Kray , Elzbieta Kryj-Kos , Gary Willard Bryant, JR. , Michael John Franks
IPC: F01D5/14
Abstract: A composite airfoil assembly for a turbine engine includes an airfoil defining an airfoil interior, and an inner support structure at least partially located within the airfoil interior. The inner support structure can include a first core, a second core, and at least one pin. A laminate overlay surrounds at least a portion of the inner support structure.
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公开(公告)号：US20240209742A1
公开(公告)日：2024-06-27
申请号：US18088990
申请日：2022-12-27
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Michael John Franks
CPC classification number: F01D5/282 , F01D5/147 , F01D5/30 , F05D2300/6034
Abstract: A composite blade assembly for a turbine engine, the composite blade assembly having a core and a laminate skin. The core having a composite structure. The laminate skin having at least one composite ply. The laminate skin having a first portion forming a first angle relative to a horizontal plane, and a second portion forming a second angle relative to the horizontal plane.
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公开(公告)号：US20230265769A1
公开(公告)日：2023-08-24
申请号：US18308806
申请日：2023-04-28
Applicant: General Electric Company
Inventor： Jason David Shapiro , Jan Christopher Schilling , Michael John Franks
CPC classification number: F01D25/246 , F01D25/24 , F01D25/12 , Y02T50/60 , F05D2220/32 , F05D2250/131 , F05D2300/50212
Abstract: A shroud hanger assembly (30) or shroud assembly is provided for dimensionally incompatible components wherein the assembly includes a multi-piece hanger (32), for example having a forward hanger portion (34) and a rearward hanger portion (36). A cavity (46) is formed between the parts; wherein a shroud (50) may be positioned which is formed of a low coefficient of thermal expansion material. The hanger (32) and shroud (50) may be formed of the same material or differing materials in order to better match the thermal growth between the hanger and the shroud. When the shroud (50) is positioned within the hanger opening or cavity (46), one of the forward (34) and rearward hanger (36) portions may be press fit or otherwise connected into the other of the forward (34) and rearward (36) hanger portion.
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公开(公告)号：US20240401486A1
公开(公告)日：2024-12-05
申请号：US18328856
申请日：2023-06-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Tod Winton Davis , Elzbieta Kryj-Kos , Michael John Franks
Abstract: A composite airfoil assembly for a gas turbine engine, the composite airfoil assembly comprising a composite airfoil, a first cladding, and a second cladding. The composite airfoil having a core comprising a composite structure having a core bulk modulus and a laminate skin applied to at least a portion of an exterior of the core. The first cladding and the second cladding are coupled to an outer surface of the composite airfoil.
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