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公开(公告)号：US11131247B2
公开(公告)日：2021-09-28
申请号：US15883336
申请日：2018-01-30
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Nitesh Jain , Srinivasarao Surapu
Abstract: A rotating shaft and a method for additively manufacturing the rotating shaft are provided. The rotating shaft includes an elongated body extending along an axial direction and including an inner surface that defines a hollow central portion. An internal support structure extends from the inner surface into the hollow central portion to stiffen the rotating shaft and provide a high stiffness-to-weight ratio. The internal support structures may include stiffening ribs, truss structures, mesh structures, solid disks, and/or regions having a decreased density relative to the elongated body. The elongated body and some or all internal features may be integrally formed as a single monolithic component.
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公开(公告)号：US10815816B2
公开(公告)日：2020-10-27
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：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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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：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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公开(公告)号：US20170321714A1
公开(公告)日：2017-11-09
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：US12264590B2
公开(公告)日：2025-04-01
申请号：US18366800
申请日：2023-08-08
Applicant: General Electric Company
Inventor： Abhijeet Jayshingrao Yadav , Nicholas Joseph Kray , Nitesh Jain
Abstract: A fan assembly for an engine has a fan blade, a disk having a disk segment, a trunnion mechanism having a trunnion extending at least partially through the disk segment, and first and second attachment systems. The trunnion has a platform and a shaft. The fan blade is adjacent to the platform of the trunnion. The trunnion is attached to the disk segment using the first attachment system along a preload path. The first and second attachment systems further include first and second retention features, respectively, separate from the preload path. During normal operation of the fan assembly, the first attachment system retains the trunnion within the disk along a first load path. Upon a failure in the trunnion, the first and second retention features together retain the trunnion within the disk segment along a second load path, the first load path being different than the second load path.
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