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公开(公告)号：US11655828B2
公开(公告)日：2023-05-23
申请号：US17511850
申请日：2021-10-27
Applicant: General Electric Company
Inventor： Li Zheng , Nicholas Joseph Kray , Changjie Sun
CPC classification number: F04D29/584 , F01D25/02 , F02C3/00 , F05D2220/323
Abstract: An airfoil for a fan section of a turbine engine may include a fan blade or an outlet guide vane, and an edge guard attached thereto. The edge guard may include a heating conduit disposed within at least a portion of the edge guard. An anti-icing system for a plurality of fan blades or outlet guide vanes may include a fluid supply pathway configured to supply heating fluid to respective ones of a plurality of heating conduits within the edge guards attached to respective ones of a plurality of fan blades and/or to a plurality of outlet guide vanes. The heating fluid may include bleed air from a core air flowpath. A method of inhibiting icing on an airfoil may include flowing a heating fluid into a heating conduit disposed within an edge guard attached to the airfoil and heating the edge guard with the heating fluid.
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公开(公告)号：US20230036022A1
公开(公告)日：2023-02-02
申请号：US17488836
申请日：2021-09-29
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Nitesh Jain
Abstract: A rotor blade for a gas turbine engine is provided. The rotor blade includes a blade body formed of a first material; and a spar within a portion of the blade body, the spar formed of a second material that is different than the first material, the spar having an elongate body including a notch. The notch, weakened geometric feature, or other reduction in cross-section defines a frangible portion of the spar that is used to control a fracture of a rotor blade.
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公开(公告)号：US20230029918A1
公开(公告)日：2023-02-02
申请号：US17490401
申请日：2021-09-30
Applicant: General Electric Company
Inventor： Abhijeet Jayshingrao Yadav , Nitesh Jain , Nicholas Joseph Kray
Abstract: An airfoil including a plurality of composite plies extending from a leading edge to a trailing edge and between a tip and a root. The airfoil further includes a frangible airfoil portion at the tip extending between the leading edge and the trailing edge and extending between the tip and a frangible line along a span. The frangible airfoil portion including a plurality of composite plies and one or more shape memory alloy inserts disposed between the plurality of composite plies. A gas turbine engine including a frangible airfoil and methods for forming a frangible airfoil are also disclosed.
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公开(公告)号：US20220341641A1
公开(公告)日：2022-10-27
申请号：US17240531
申请日：2021-04-26
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Thomas J. Brinck , Tod W. Davis , Chad M. Harbert
IPC: F25C1/04
Abstract: Methods and apparatus for artificial bird manufacturing in impact testing is described herein. An apparatus to generate an artificial bird for impact testing includes a mold generator to form a mold based on a bird class identification, a mold filler to fill the mold with a first layer of crushed ice and a second layer of crushed ice, a compressor to compress an ice surface of at least one of the first layer or the second layer of the crushed ice to form indentations on the ice surface, and a freezer to re-freeze the crushed ice layers inside the mold to form an artificial bird.
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245.发明申请公开(公告)号：US20220290572A1
公开(公告)日：2022-09-15
申请号：US17198843
申请日：2021-03-11
Applicant: General Electric Company
Inventor： Anthony Michael Gunasekera , Nicholas Joseph Kray , Leslie Louis Langenbrunner , Simeon Paul Copple
Abstract: A composite airfoil having a non-metallic leading edge protective wrap is provided. In one aspect, the airfoil has a composite core having a pressure sidewall and a suction sidewall each extending between a core leading edge and a core trailing edge. A leading edge protective wrap protects the core leading edge and includes a trailing wrap and a leading wrap. The trailing wrap wraps around the core leading edge and is connected to the composite core. The leading wrap wraps around the core leading edge and is connected to the trailing wrap. The trailing and leading wraps both have leading edges that are spaced from one another. A filler is positioned between the leading edges of the trailing and leading wraps. A protective nose is connected to the leading edge of the leading wrap. The components of the leading edge protective wrap are formed of non-metallic materials.
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Patent Agency Ranking
公开(公告)号：US11371433B2
公开(公告)日：2022-06-28
申请号：US16550721
申请日：2019-08-26
Applicant: General Electric Company
IPC: F02C7/047 , F01D5/28 , F01D5/14 , F04D29/38 , B32B5/02 , B32B5/26 , B32B38/18 , B32B3/06 , B32B5/12 , B32B7/02 , B32B19/02 , B32B19/06 , B32B3/08 , B29C70/88 , F02K3/06
Abstract: Composite components and methods for forming composite components are provided. For example, a composite component of a gas turbine engine comprises a composite material, a plurality of piezoelectric fibers, and an anti-icing mechanism. The anti-icing mechanism is in operative communication with the piezoelectric fibers such that the anti-icing mechanism is activated by one or more electrical signals from the piezoelectric fibers. In exemplary embodiments, the composite component is a composite airfoil and the anti-icing mechanism is one or more heating elements. Methods for forming composite components may comprise forming piezoelectric plies comprising piezoelectric fibers embedded in a matrix material; forming reinforcing plies comprising reinforcing fibers embedded in the matrix material; laying up the piezoelectric and reinforcing plies to form a ply layup; and processing the ply layup to form the composite component. Methods including forming a piece of piezoelectric material that is adhered to a composite component also are provided.
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公开(公告)号：US11286807B2
公开(公告)日：2022-03-29
申请号：US16145656
申请日：2018-09-28
Applicant: General Electric Company
Inventor： Nitesh Jain , Abhijit Roy , Kishore Budumuru , Nicholas Joseph Kray
Abstract: A blade for a propulsion apparatus that includes a body formed of a first material having opposed pressure and suction sides, and extending in span between a root and a boundary, and extending in chord between a leading edge and a trailing edge. A tip region that is formed of a second material and that is positioned such that it extends from the body and defines a tip. The tip region joins the body at the boundary. The tip region is configured to fail when a predetermined force is applied to the tip such that the tip separates from the blade and defines a fused tip.
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公开(公告)号：US20220074344A1
公开(公告)日：2022-03-10
申请号：US17365855
申请日：2021-07-01
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Sreekanth Kumar Dorbala , Nitesh Jain , Prashant Sharma
Abstract: A booster splitter for a gas turbine engine and a method of additively manufacturing the booster splitter are provided. The booster splitter includes an annular inner wall defining a radially outer boundary of a compressor flow path defined through a compressor section of the gas turbine engine, an annular outer wall spaced apart from the annular inner wall along the radial direction, the annular outer wall adjacent to the annular inner wall at a forward end, the forward end defining an inlet to the compressor flow path, an annular bulkhead spanning between the annular inner wall and the annular outer wall substantially along the radial direction, the bulkhead defining an inlet port, and a passageway defined within the annular outer wall, the passageway extending from the inlet port, into the bulkhead, radially outward to the outer wall, and through the annular outer wall towards the inlet defined by the forward end.
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公开(公告)号：US20220065118A1
公开(公告)日：2022-03-03
申请号：US17410739
申请日：2021-08-24
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Ian F. Prentice
Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed to adjust a pitch axis of a blade of an engine. An example blade apparatus includes: a hub to facilitate movement of blades in an engine, the engine having a radial center line; and a trunnion connected to the hub. The example trunnion includes a slot to accommodate a first blade, and at least one of the trunnion or the first blade is positioned with at least one of a tilt or a lean with respect to the radial center line to form a pitch axis offset from the radial center line such that the pitch axis is not parallel to or co-linear with the radial center line. The example hub is to rotate the first blade about the pitch axis.
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公开(公告)号：US20220065117A1
公开(公告)日：2022-03-03
申请号：US17410727
申请日：2021-08-24
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Ian F. Prentice
Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed for a slot to accommodate a blade of an engine. An example apparatus includes: a socket to receive an end of a blade; and a retaining device to interact with the socket and the blade for retention of the end of the blade in the socket. The example retaining device includes: a spacer to be positioned in the socket with the end of the blade; a wedge positioned inside the spacer; and a spring to tighten to pull the wedge to expand the spacer.
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