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公开(公告)号：US10815798B2
公开(公告)日：2020-10-27
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 made of materials with different elasticity and mounted to the core leading edge.
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公开(公告)号：US10731470B2
公开(公告)日：2020-08-04
申请号：US15806871
申请日：2017-11-08
Applicant: General Electric Company
Inventor： David William Crall
Abstract: An airfoil defining a chordwise dimension, a spanwise dimension, a leading edge, a trailing edge, a root, and a tip, is generally provided. The airfoil includes a first material substrate defining a pressure side and a suction side. The first material substrate defines a plurality of discrete volumes extended from at least one of the pressure side or the suction side into the first material substrate. The plurality of discrete volumes is arranged at least partially along the chordwise dimension and a second material substrate different from the first material substrate is defined at least partially within the volume.
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公开(公告)号：US20200182062A1
公开(公告)日：2020-06-11
申请号：US16213653
申请日：2018-12-07
Applicant: General Electric Company
Inventor： Gregory Carl Gemeinhardt , Douglas Duane Ward , David William Crall , Nicholas Joseph Kray
Abstract: An airfoil that includes an airfoil body having a root and a tip, and convex and concave sides that extend between a leading edge and a trailing edge. The airfoil also includes at least a first cladding element that is attached to the airfoil body. The first cladding element includes a first portion and a second portion. The second portion is configured to separate from the first portion when the first cladding element encounters a force of at least a predetermined amount.
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公开(公告)号：US10385870B2
公开(公告)日：2019-08-20
申请号：US15105212
申请日：2014-11-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： David William Crall
Abstract: A ribbed composite shell includes an annular grid of relatively thick crack arresting ribs embedded in a relatively thin annular shell and relatively thin panels in thin annular shell between arresting ribs wherein each of panels are completely surrounded by a set of relatively thick adjoining ones of ribs. A shell forward flange may extend radially inwardly from thin annular shell. Arresting ribs may include radially stacked layers of strips between radially stacked annular layers of shell. Annular grid may include a rectangular grid pattern, a diamond grid pattern, or a hexagonal grid pattern. A nacelle inlet may have the ribbed composite shell within one or both of radially spaced apart composite inner and outer skins of an inner barrel. Nacelle inlet may be part of attached to a fan casing and axially disposed forward of fan blades circumscribed by the casing. The inlet may be on an engine nacelle.
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公开(公告)号：US20180363677A1
公开(公告)日：2018-12-20
申请号：US15625186
申请日：2017-06-16
Applicant: General Electric Company
Inventor： Christopher James Kroger , Brandon Wayne Miller , Trevor Wayne Goerig , David William Crall , Tsuguji Nakano , Jeffrey Donald Clements , Bhaskar Nanda Mondal
Abstract: A gas turbine engine includes a turbomachine and a fan rotatable by the turbomachine. The fan includes a plurality of fan blades. The gas turbine engine also includes an outer nacelle surrounding the plurality of fan blades and a plurality of part-span inlet guide vanes cantilevered from the outer nacelle at a location forward of the plurality of fan blades along the axial direction. Each of the plurality of inlet guide vanes defines an inner end along the radial direction and it is unconnected with an adjacent part-span inlet guide vane at the inner end.
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Patent Agency Ranking
公开(公告)号：US12116903B2
公开(公告)日：2024-10-15
申请号：US17363102
申请日：2021-06-30
Applicant: General Electric Company
Inventor： Nitesh Jain , Nicholas Joseph Kray , Daniel Edward Mollmann , David William Crall
CPC classification number: F01D5/147 , F01D5/282 , F01D5/284 , F01D21/045 , F05D2220/36 , F05D2240/304 , F05D2240/307 , F05D2300/6033
Abstract: Composite airfoils and methods for forming composite airfoils are provided. For example, a composite airfoil of a gas turbine engine comprises opposite pressure and suction sides extending radially along a span from a root to a tip, which define opposite radial extremities of the airfoil. The composite airfoil further comprises a body section and a tip section, which includes the tip, that each extend radially along the span. The composite airfoil is formed from a composite material comprising fibers disposed in a matrix material. The tip section has a tip fiber volume, and the body section has a body fiber volume that is greater than the tip fiber volume. Another composite airfoil comprises a tip cap applied over the tip that tapers from a first end to a second end such that each of the pressure and suction side walls of the tip cap narrows from a first thickness to a second thickness.
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公开(公告)号：US11286782B2
公开(公告)日：2022-03-29
申请号：US16213653
申请日：2018-12-07
Applicant: General Electric Company
Inventor： Gregory Carl Gemeinhardt , Douglas Duane Ward , David William Crall , Nicholas Joseph Kray
Abstract: An airfoil that includes an airfoil body having a root and a tip, and convex and concave sides that extend between a leading edge and a trailing edge. The airfoil also includes at least a first cladding element that is attached to the airfoil body. The first cladding element includes a first portion and a second portion. The second portion is configured to separate from the first portion when the first cladding element encounters a force of at least a predetermined amount.
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公开(公告)号：US20210339846A1
公开(公告)日：2021-11-04
申请号：US17071308
申请日：2020-10-15
Applicant: General Electric Company
IPC: B64C1/38
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：US11149584B2
公开(公告)日：2021-10-19
申请号：US16594208
申请日：2019-10-07
Applicant: General Electric Company
Inventor： David William Crall , Nicholas Joseph Kray , Scott Roger Finn , Wendy Wenling Lin
IPC: F01D21/04
Abstract: Containment assemblies and methods for forming containment assemblies of gas turbine engines are provided. For example, a containment assembly comprises a containment case including a plurality of coated fibers. Each coated fiber comprises a fiber surrounded by a ceramic material such that the ceramic material coats the fiber. As another example, a containment assembly comprises an inner case and a containment case comprising a plurality of coated fibers. Each coated fiber comprises a fiber surrounded by a ceramic material such that the ceramic material coats the fiber. The containment case includes a greater proportion of the coated fibers at an inner surface of a layer of the containment case than at a location within the containment case that is radially outward from the inner surface. Methods for forming a containment assembly of a gas turbine engine are provided.
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公开(公告)号：US20210102475A1
公开(公告)日：2021-04-08
申请号：US16594208
申请日：2019-10-07
Applicant: General Electric Company
Inventor： David William Crall , Nicholas Joseph Kray , Scott Roger Finn , Wendy Wenling Lin
IPC: F01D25/26
Abstract: Containment assemblies and methods for forming containment assemblies of gas turbine engines are provided. For example, a containment assembly comprises a containment case including a plurality of coated fibers. Each coated fiber comprises a fiber surrounded by a ceramic material such that the ceramic material coats the fiber. As another example, a containment assembly comprises an inner case and a containment case comprising a plurality of coated fibers. Each coated fiber comprises a fiber surrounded by a ceramic material such that the ceramic material coats the fiber. The containment case includes a greater proportion of the coated fibers at an inner surface of a layer of the containment case than at a location within the containment case that is radially outward from the inner surface. Methods for forming a containment assembly of a gas turbine engine are provided.
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