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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：US11149558B2
公开(公告)日：2021-10-19
申请号：US16161200
申请日：2018-10-16
Applicant: General Electric Company
Inventor： Nitesh Jain , Nicholas Joseph Kray , Kishore Budumuru
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 including a first plurality of composite plies. Each of the first plurality of composite plies includes fibers oriented at least partially along a chordwise direction, a thickness direction, or both. The airfoil further includes a residual airfoil portion extending from the frangible line to the root along the span including a second plurality of composite plies. The second plurality of composite plies includes at least one composite ply with fibers oriented along the span. Further, the residual airfoil portion meets the frangible airfoil portion at the frangible line.
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公开(公告)号：US11111815B2
公开(公告)日：2021-09-07
申请号：US16161253
申请日：2018-10-16
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Nitesh Jain , Daniel Edward Mollmann
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 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 the span. The frangible airfoil portion includes an exterior surface. The exterior surface at least partially defines at least one fusion cavity at least partially defining the frangible line. The airfoil further includes a residual airfoil portion extending from the frangible line to the root along the span. The residual airfoil portion meets the frangible airfoil portion at the frangible line. As such, the frangible airfoil portion deforms or partially or fully detaches relative to the residual airfoil portion at the frangible line following an event creating imbalance.
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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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公开(公告)号：US10938328B2
公开(公告)日：2021-03-02
申请号：US15189026
申请日：2016-06-22
Applicant: General Electric Company
Inventor： Aaron Todd Sellinger , Nicholas Joseph Kray
IPC: H02N2/18 , H01L41/113 , F04D29/38 , H01L35/32 , G01L1/16 , G01K7/02 , F01D5/28 , F01D15/10 , F01D5/16 , C04B35/52 , C04B35/117 , F03G7/08 , C04B35/565 , F01D25/00 , C04B35/80 , F01D25/04 , F01D5/10 , F01D25/06 , F01D5/26
Abstract: The present disclosure is directed to an engine component for a gas turbine engine, the engine component including a substrate that includes a composite fiber and defines a surface. An energy harvesting fiber is positioned within the substrate.
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Patent Agency Ranking
公开(公告)号：US20200378273A1
公开(公告)日：2020-12-03
申请号：US16424843
申请日：2019-05-29
Applicant: General Electric Company
Inventor： Abhijeet Jayshingrao Yadav , Nagamohan Govinahalli Prabhakar , Nicholas Joseph Kray , Shivam Mittal , Praveen Sharma , Bhujabal Prashant Mahadeo , Ravindra Shankar Ganiger
Abstract: A composite fan casing for a gas turbine engine defining a central axis is generally provided. The composite fan casing includes a core having a plurality of core layers of reinforcing fibers bonded together with a thermosetting polymeric resin and having an outer surface. The composite fan casing further includes at least one stiffener integrally coupled to an aft portion of the outer surface of the core relative to the central axis. Additionally, the at least one stiffener comprises an elastic material.
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公开(公告)号：US10703452B2
公开(公告)日：2020-07-07
申请号：US15295601
申请日：2016-10-17
Applicant: General Electric Company
Abstract: An apparatus and system for a marine propeller assembly are provided. An aft retention member that may be used with the marine propeller assembly includes a base, an opposing nose and a conic body extending therebetween along a centerline normal to the base. The aft retention member also includes at least one protuberance extending radially away from a surface of the conic body. The protuberance extends axially along a surface of the aft retention member from the base arcuately convergent to a predetermined point between the base and a tip of the nose.
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公开(公告)号：US20200157953A1
公开(公告)日：2020-05-21
申请号：US16196288
申请日：2018-11-20
Applicant: General Electric Company
Inventor： Nitesh Jain , David William Crall , Nicholas Joseph Kray
Abstract: A blade for a propulsion apparatus. The blade includes a body formed of a composite material and the body has opposed pressure and suction sides. The body extends in span between a root and a tip and extends in chord between a leading edge and a trailing edge. The body defines a body tip surface. A protective cover extends from near the tip of the blade toward the root of the blade along the leading edge and a trailing edge of the body. The protective cover defines a protective tip surface and an abrasive material is adhered to the protective tip surface.
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公开(公告)号：US20200095883A1
公开(公告)日：2020-03-26
申请号：US16139645
申请日：2018-09-24
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Nitesh Jain , Manoj Kumar Jain
Abstract: A propulsion system including a casing surrounding a fan rotor assembly is provided. The casing includes an outer layer material defining a first coefficient of thermal expansion (CTE) and an inner layer material. The casing further includes a spring member disposed between the outer layer material and the inner layer material coupling the outer layer material and the inner layer material. The spring member is coupled to each of the outer layer material and the inner layer material within a flow passage defined between the outer layer material and the inner layer material. The spring member defines a second CTE greater than the first CTE.
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公开(公告)号：US10450870B2
公开(公告)日：2019-10-22
申请号：US15018902
申请日：2016-02-09
Applicant: General Electric Company
Inventor： Phani Nandula , Suresh Subramanian , Nicholas Joseph Kray , Gregory Carl Gemeinhardt
Abstract: An airfoil for an aircraft engine is provided. The airfoil may include a plurality of composite plies extending in a chordwise direction from a leading edge to a trailing edge and in a spanwise direction between an airfoil tip and an airfoil base. The airfoil may include at least one discontinuous ply having a first ply segment, a second ply segment, and a butt joint disposed between the first ply segment and the second ply segment. The butt joint may be disposed along a first fragment profile to frangibly attach the first and second ply segments.
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