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公开(公告)号：US10760428B2
公开(公告)日：2020-09-01
申请号：US16161296
申请日：2018-10-16
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Nitesh Jain
Abstract: An airfoil defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge. The airfoil includes a leading edge sheath coupled to the leading edge of the airfoil. The leading edge sheath includes a flange extending from a frangible line toward the tip along the span and defining a first width along the chord at each point along the span S. The leading edge sheath further includes a base extending from the frangible line at least partially along the span to the root and defining a second width along the chord at a point along the span of the frangible line such that the second width is greater than the first width.
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公开(公告)号：US10724376B2
公开(公告)日：2020-07-28
申请号：US15891401
申请日：2018-02-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Nitesh Jain , Nagashiresha Gontla , Narendra Digamber Joshi , Paul Gerard Marsland , Wayne Allen Spence
Abstract: A blade and a turbomachine engine having the blade are disclosed. The blade includes an airfoil having a root portion, a tip portion, and a plurality of fins integrally coupled to the root portion. The plurality of fins is disposed along a thickness of the airfoil.
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263.发明授权公开(公告)号：US10697470B2
公开(公告)日：2020-06-30
申请号：US15043881
申请日：2016-02-15
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Douglas Duane Ward
Abstract: A containment case includes a fan assembly including a hub having a plurality of fan blades extending radially outward between radially inward blade roots and radially outward blade tips. Containment case includes a radially outer shell circumscribing fan assembly and having a first radially inner surface and a radially outer surface, an inner structure having a second radially inner surface extending along first radially inner surface, and a trench extending circumferentially along second radially inner surface into inner structure from second radially inner surface. The trench is approximately axially aligned with the fan assembly. The containment case also includes, within the trench, a trench filler layer configured to dissipate impact energy from a released fan blade and having a plurality of sheets including a fibrous composite material having a plurality of fibers fabricated within each sheet, where the sheets are coupled together into a repeating pattern of hollow units.
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公开(公告)号：US10689073B2
公开(公告)日：2020-06-23
申请号：US15295679
申请日：2016-10-17
Applicant: General Electric Company
Abstract: An apparatus and system for a marine propeller assembly are provided. In one aspect, the marine propeller assembly includes a plurality of circumferentially-spaced blades that each include a dovetail having a radial inner surface. The marine propeller assembly also includes a hub including a plurality of circumferentially-spaced dovetail receiving portions configured to receive a corresponding dovetail of the plurality of blades. At least one gap is formed between the radial inner surface and at least a portion of the dovetail receiving portion.
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公开(公告)号：US10662813B2
公开(公告)日：2020-05-26
申请号：US15486946
申请日：2017-04-13
Applicant: General Electric Company
Inventor： Thomas Chadwick Waldman , James Edward Thompson , Douglas Ward , Nicholas Joseph Kray , Scott Roger Finn , Apostolos Pavlos Karafillis
Abstract: A turbine engine that includes an engine casing including a shell and an angel wing member. The angel wing member includes a base defined at the shell and a tip positioned distal from the base. The turbine engine also includes a backsheet extending over the angel wing member such that an angled region is defined in the backsheet at an interface with the tip. The tip has a predetermined contour capable of mitigating stress concentrations in the angled region induced from said tip.
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Patent Agency Ranking
公开(公告)号：US20200132087A1
公开(公告)日：2020-04-30
申请号：US16170254
申请日：2018-10-25
Applicant: General Electric Company
Inventor： Arun Kumar , Nitesh Jain , Nicholas Joseph Kray , Thomas Ory Moniz , Andrew Breeze-Stringfellow
Abstract: A noise reducing airfoil defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge. The airfoil includes a pressure side, a suction side, and a trailing edge sheath including an outer surface coupled to the trailing edge of the airfoil. The trailing edge sheath extends at least partially along the chord on the pressure and suction sides at each point along the span within the trailing edge sheath. The trailing edge sheath defines a fluid passageway extending along at least a portion of the span. Further, the trailing edge sheath defines at least one aperture on at least one of the pressure side, the suction side, or trailing edge fluidly coupling the fluid passageway to the outer surface.
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公开(公告)号：US20200116046A1
公开(公告)日：2020-04-16
申请号：US16161270
申请日：2018-10-16
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Nitesh Jain
Abstract: An airfoil defining a span extending between a root and a tip. The airfoil includes a retaining member extending at least partially between a leading edge and a trailing edge defining a frangible line extending at least partially along a chord at a point along the span of the retaining member. The airfoil further includes a frangible airfoil portion extending between the tip and the frangible line. The frangible airfoil portion includes a first plurality of composite plies, at least one composite ply of the first plurality of composite plies wraps around the retaining member. The airfoil includes a residual airfoil portion extending from the frangible line to the root including a second plurality of composite plies, at least one composite ply of the second plurality of composite plies wraps around the retaining member. Further, the residual airfoil portion meets the frangible airfoil portion at the frangible line.
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公开(公告)号：US10539025B2
公开(公告)日：2020-01-21
申请号：US15040582
申请日：2016-02-10
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Trevor Howard Wood , Dong-Jin Shim , Pranav Dhoj Shah
Abstract: An airfoil assembly including a composite body having a mounting edge and a trailing edge which is secured to a leading edge element defining a 3-D leading edge geometry with both chord and camber variation.
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公开(公告)号：US20190390600A1
公开(公告)日：2019-12-26
申请号：US16015468
申请日：2018-06-22
Applicant: GENERAL ELECTRIC COMPANY
Abstract: An aircraft can include a turbine engine including a rotor and a stator, and also including a compressor, a combustor, and a turbine in axial flow arrangement. The aircraft can further include an anti-icing system with a magnetic field generator having a rotating portion and a non-rotating portion, as well as an array of carbon nanotubes thermally coupled to an exposed surface.
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公开(公告)号：US10436061B2
公开(公告)日：2019-10-08
申请号：US15486789
申请日：2017-04-13
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Thomas Chadwick Waldman , Manoj Kumar Jain , Mojibur Rahman , Nitesh Jain , Nagamohan Govinahalli Prabhakar , Scott Roger Finn , Apostolos Pavlos Karafillis
Abstract: A backsheet for use in a turbine engine fan case includes a first portion including a first portion first end and an opposing first portion second end. The first portion is tapered between the first portion first end and the first portion second end. The backsheet also includes a second portion coupled to the first portion. The second portion includes a second portion first end and an opposing second portion second end. The second portion defines a constant thickness between the second portion first end and the second portion second end.
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