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公开(公告)号：US20200011203A1
公开(公告)日：2020-01-09
申请号：US16028867
申请日：2018-07-06
Applicant: General Electric Company
Inventor： Nagamohan Govinahalli Prabhakar , Manoj Kumar Jain , Nitesh Jain , Uma Maheshwar Domala , Nicholas Joseph Kray
Abstract: A blade containment structure surrounding a fan in a turbofan engine is disclosed. The blade containment structure includes a cellular material to absorb energy and contain fragments of a blade thrown outward; an inner shell; a ductile back sheet spaced radially outward from the inner shell, the ductile back sheet and inner shell cooperating to define a nesting area for the cellular material, wherein the cellular material is bound at its radially inner surface by the inner shell and at its outer surface by the ductile back sheet; and a containment blanket overlaid on the ductile back sheet, the containment blanket being of the type effective to contain fragments of the blade that penetrate through the ductile back sheet.
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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：US10927703B2
公开(公告)日：2021-02-23
申请号：US15705712
申请日：2017-09-15
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Benjamin James Roby , Vijesh Shetty Anangoor , Nitesh Jain , Sreekanth Kumar Dorbala , Nagamohan Govinahalli Prabhakar , K Phani SriKrishna Chinnapragada
Abstract: Fan blade containment system includes a composite fan case with an annular composite shell extending from forward flange downstream to aft flange, and circumferentially varying thickness portion of composite shell. Annular composite back sheet spaced radially outwardly of annular composite shell has annular filler layer disposed radially therebetween. Annular forward and aft seams between annular composite shell and composite back sheet may axially trap filler layer. Circumferentially varying thickness portion may include aftwardly extending fingers of composite back sheet in aft seam and first thickness of fingers thicker than second thickness of composite shell circumferentially between fingers. Composite shell may extend from forward flange to aft flange. Aft flange bolted to metallic flange of metallic fan casing aft of aft flange. Containment system may circumscribe and surround fan and fan blades of gas turbine engine fan section.
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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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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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Patent Agency Ranking
公开(公告)号：US10801361B2
公开(公告)日：2020-10-13
申请号：US15260641
申请日：2016-09-09
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nagamohan Govinahalli Prabhakar , Steven Andrew Strang , Charles Stanley Orkiszewski , Subramanya Shankar , Nitesh Jain , Michael Riehle
Abstract: The turbine assembly includes a shaft, a plurality of rotor disks, a plurality of blades, and at least one cutting mechanisms. The rotor disks are spaced axially along, and coupled to, the shaft and include a radially outer portion. The blades are spaced circumferentially around the radially outer portion. The cutting mechanisms are configured to cut the blades from the rotor disk during a disk over speed condition.
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公开(公告)号：US20180340447A1
公开(公告)日：2018-11-29
申请号：US15605297
申请日：2017-05-25
Applicant: General Electric Company
Inventor： Apostolos Pavlos Karafillis , Manoj Kumar Jain , Thomas Chadwick Waldman , Nagamohan Govinahalli Prabhakar
Abstract: A bolted joint apparatus includes: a first component including a first row of first bolt holes extending therethrough; a second component including a second row of second bolt holes extending therethrough wherein the second bolt holes are aligned coaxially with the first bolt holes, a plurality of fasteners, each of fasteners disposed through aligned pairs of the first and second bolt holes to couple together the first and second components, each of the fasteners including a shank; and crushable spacers disposed around the shanks of the fasteners, the crushable spacers clamped in compression between the fasteners and one of the components, wherein each of the crushable spacers has a tubular body interconnecting first and second enlarged ends, the tubular body being defined by a peripheral wall which incorporates at least one weakening feature.
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公开(公告)号：US20180334922A1
公开(公告)日：2018-11-22
申请号：US15596523
申请日：2017-05-16
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
CPC classification number: F01D21/045 , F01D25/24 , F02C3/04 , F02K3/06 , F05D2220/323 , F05D2240/14 , F05D2300/501
Abstract: A softwall containment system for a machine includes an inner wall circumscribing a bladed rotatable member of the machine and extending from a forward end to an aft end. The softwall containment system also includes an outer wall circumscribing the inner wall and extending from a forward end to an aft end. The outer wall is spaced radially outwardly from the inner wall. The outer wall extends axially between a first joint coupling the forward end of the inner wall to the forward end of the outer wall and a second joint coupling the aft end of the inner wall to the aft end of the outer wall. The softwall containment system also includes an anti-ballistic material wrap covering the outer wall, the anti-ballistic material wrap including at least one of a first extension extending forward of the first joint and a second extension extending aft of the second joint.
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公开(公告)号：US20180073388A1
公开(公告)日：2018-03-15
申请号：US15260641
申请日：2016-09-09
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nagamohan Govinahalli Prabhakar , Steven Andrew Strang , Charles Stanley Orkiszewski , Subramanya Shankar , Nitesh Jain , Michael Riehle
Abstract: The turbine assembly includes a shaft, a plurality of rotor disks, a plurality of blades, and at least one cutting mechanisms. The rotor disks are spaced axially along, and coupled to, the shaft and include a radially outer portion. The blades are spaced circumferentially around the radially outer portion. The cutting mechanisms are configured to cut the blades from the rotor disk during a disk over speed condition.
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公开(公告)号：US11242866B2
公开(公告)日：2022-02-08
申请号：US16051943
申请日：2018-08-01
Applicant: General Electric Company
Inventor： Manoj Kumar Jain , Nagamohan Govinahalli Prabhakar , Scott Roger Finn
IPC: F04D29/52 , F01D25/00 , F01D21/04 , F04D29/02 , B32B27/08 , B32B27/20 , B29C70/30 , F01D25/26 , B29L31/00
Abstract: Walls of gas turbine engine casings, fan cases, and methods for forming walls, e.g., fan case walls, are provided. For example, a wall comprises a plurality of composite plies arranged in a ply layup. The wall is annular and circumferentially segmented into a plurality of regions that include at least one first region and at least one second region. The ply layup in the first and second regions is different such that the ply layup is non-axisymmetric. An exemplary fan case comprises an annular inner shell, a filler layer, an annular back sheet, and an annular outer layer. The back sheet is circumferentially segmented into a plurality of regions, including at least one first region and at least one second region, and comprises a plurality of composite plies arranged in a ply layup that is different in the first and second regions such that the ply layup is non-axisymmetric.
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