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公开(公告)号：US10677261B2
公开(公告)日：2020-06-09
申请号：US15487003
申请日：2017-04-13
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Thomas Chadwick Waldman , James Edward Thompson , Douglas Ward , 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, a tip positioned distal from the base, and a first side and a second side that define a thickness of the angel wing member. The thickness of the angel wing member is non-uniform between the base and the tip.
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公开(公告)号：US10677260B2
公开(公告)日：2020-06-09
申请号：US15438284
申请日：2017-02-21
Applicant: General Electric Company
Inventor： Veeraraju Vanapalli , Nitesh Jain , Viswanadha Gupta Sakala , Bhaskar Nanda Mondal , Nicholas Joseph Kray
Abstract: A turbine engine that includes a rotor assembly including a plurality of rotor blades, an outer case positioned radially outward from the plurality of rotor blades, and an annular ring coupled to the outer case and positioned between the plurality of rotor blades and the outer case. The annular ring is configured to restrict thermal contraction of the outer case towards the plurality of rotor blades.
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公开(公告)号：US10677259B2
公开(公告)日：2020-06-09
申请号：US15148631
申请日：2016-05-06
Applicant: General Electric Company
Inventor： Nitesh Jain , Vikulp Sharma , Nicholas Joseph Kray
Abstract: A metal leading edge includes a nose positioned along the leading edge of a fan blade airfoil body. The metal leading edge also includes a first edge extending axially aftward from the nose along a pressure side of the fan blade airfoil body. The metal leading edge further includes a second edge extending axially aftward from the nose along a suction side of the fan blade airfoil body. The first edge and the second edge forming a notch at the conjunction of the first edge, the second edge, and the nose. The metal leading edge also includes a nose length extending from a nose tip to the notch. The nose length at a first radial location is different from the nose length at a second radial location.
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公开(公告)号：US20200149399A1
公开(公告)日：2020-05-14
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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公开(公告)号：US10589475B2
公开(公告)日：2020-03-17
申请号：US14860132
申请日：2015-09-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Xiaomei Fang , Christopher Madsen , Ian Francis Prentice , Sultan Shair , Dong-Jin Shim , Douglas Duane Ward
Abstract: A gas turbine engine composite article having a composite article airfoil extending outwardly to an article root to an article airfoil tip. Within the article airfoil is a core including a core airfoil attached to a core root including a core dovetail. A continuous outer three-dimensional braided layer including braided composite material tows are braided on the core and the braided layer covers the entire core airfoil and the core root. The core may be an inflatable mandrel or a composite core made of a composite material. The core may include stiffeners such as an I beam or hollow rectangular cross-section box beams. A method for making such an article includes braiding a continuous outer three-dimensional braided layer including braided composite material tows on the core including covering the entire core airfoil and the core root with the continuous outer three-dimensional braided layer.
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Patent Agency Ranking
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：US20190257210A1
公开(公告)日：2019-08-22
申请号：US15898690
申请日：2018-02-19
Applicant: General Electric Company
Inventor： Qiang Li , Nicholas Joseph Kray , Gerald Alexander Pauley , Ming Xie , Jorge Orlando Lamboy , Tod Winton Davis
Abstract: A platform apparatus for a propulsion rotor having an annular array of airfoils carried by a rotor disk. The apparatus includes: at least one forward segment comprising an arcuate forward body having a plurality of spaced-apart axially-extending forward fingers, each of the forward fingers bounded by a curved first lateral edge interconnected to a straight second lateral edge by an aft edge, wherein the forward segment defines a flow path surface and an opposed back surface; at least one aft segment comprising an arcuate aft body having a plurality of spaced-apart actually-extending aft fingers, each of the aft fingers bounded by a curved first lateral edge interconnected to a straight second lateral edge by a forward edge, wherein the aft segment defines a flow path surface and an opposed back surface, and wherein the aft edges have a shape complementary to a shape of the forward edges.
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公开(公告)号：US10328639B2
公开(公告)日：2019-06-25
申请号：US15017104
申请日：2016-02-05
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Stefaan Guido Van Nieuwenhove
Abstract: An automated fiber placement (AFP) system includes a tool head with a compaction roller and a first variable heat source. The compaction roller is configured to receive at least one of a fiber and a plurality of fibers formed as a laydown tape, and is controlled to apply the laydown tape to a workpiece at a predetermined speed and direction. The first variable heat source is configured to apply a first amount of heat to the laydown tape. The first amount of heat applied is related to the predetermined speed. The AFP system further includes a second variable heat source configured to apply a second amount of heat to the workpiece. The second amount of heat applied is related to at least one of: a position on the workpiece, a thickness of the workpiece at that position, and a separation distance between the second variable heat source and the workpiece.
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公开(公告)号：US20190170012A1
公开(公告)日：2019-06-06
申请号：US15832814
申请日：2017-12-06
Applicant: General Electric Company
Abstract: A rotor assembly includes a fan rotor shaft coupled to a fan rotor, a low pressure turbine rotor shaft coupled to a low pressure turbine rotor, and a joint device configured to connect the fan rotor shaft to the low pressure turbine rotor shaft, to allow torsion, shear and bending to be transferred between the fan rotor shaft and the low pressure turbine rotor shaft under normal operation, and allow torsion and shear but prevent bending to be transferred between the fan rotor shaft and the low pressure turbine rotor shaft under a fan blade-out event.
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公开(公告)号：US20180283180A1
公开(公告)日：2018-10-04
申请号：US15471729
申请日：2017-03-28
Applicant: General Electric Company
Inventor： Nitesh Jain , Abhijeet Jayshingrao Yadav , Kishore Budumuru , Nicholas Joseph Kray
Abstract: A turbine engine can comprise a fan section, compressor section, a combustion section, and a turbine section in axial flow arrangement. At least one of the fan section and compressor section can include an airfoil with a leading edge, and a plurality of riblets can be arranged on the leading edge.
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