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公开(公告)号：US20220316342A1
公开(公告)日：2022-10-06
申请号：US17844578
申请日：2022-06-20
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Viswanadha Gupta Sakala , Nicholas Joseph Kray , Ambika Shivamurthy , Kirti Arvind Petkar
Abstract: Methods, apparatus, systems and articles of manufacture corresponding to a fan blade with intrinsic damping characteristics are disclosed. An example fan blade comprises an exterior body including a first side and a second side; a first hairpin structure in contact with (a) the first side of the exterior body and (b) the second side of the exterior body; and a second hairpin structure in contact with (a) the first side and (b) the second side, wherein the first hairpin structure and the second hairpin structure are made from different materials.
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公开(公告)号：US20210363888A1
公开(公告)日：2021-11-25
申请号：US16923911
申请日：2020-07-08
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Viswanadha Gupta Sakala , Nicholas Joseph Kray , Ambika Shivamurthy , Kirti Arvind Petkar
Abstract: Methods, apparatus, systems and articles of manufacture corresponding to a fan blade with intrinsic damping characteristics are disclosed. An example fan blade comprises an exterior body including a first side and a second side; a first hairpin structure coupled to the first side of the exterior body and the second side of the exterior body; and a second hairpin structure coupled to the first side and the second side, the first hairpin structure in contact with the second hairpin structure.
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公开(公告)号：US20190389589A1
公开(公告)日：2019-12-26
申请号：US16015283
申请日：2018-06-22
Applicant: GENERAL ELECTRIC COMPANY
Abstract: An aircraft can include an anti-icing system. The anti-icing system can include an array of carbon nanotubes thermally coupled to at least a first exposed surface of the aircraft. The anti-icing system can also include an array of solar cells carried by the aircraft and electrically coupled to the array of carbon nanotubes.
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公开(公告)号：US20180265181A1
公开(公告)日：2018-09-20
申请号：US15458354
申请日：2017-03-14
Applicant: General Electric Company
Inventor： Abhishek Goverdhan , Ravindra Shankar Ganiger , Richa Awasthi , Viswanadha Gupta Sakala , Vidya Lokammanahalli Shivashankar
Abstract: An aircraft spinner assembly includes collar stud joints connecting spinner to forward flange connected to fan rotor disk. Collar stud joint is operable to push out spinner when stud is un-torqued. Collar may be attached to stud disposed through spinner bolt hole in spinner and collar disposed in counterbore of spinner bolt hole. An aft stud thread on collar stud may be threaded into aft nut which may be swaged into flange bolt hole in forward flange. A washer may be in counterbore between collar and spinner and made from low friction and/or sacrificial material. A forward radial clearance may surround stud between stud and spinner. A forward nut may be threaded onto forward stud threads on forward end of the collar stud and abut spinner. External aft stud threads may be on collar studs and threaded into internal flange threads within flange bolt holes in forward flange.
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公开(公告)号：US20180238346A1
公开(公告)日：2018-08-23
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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Patent Agency Ranking
公开(公告)号：US12110805B2
公开(公告)日：2024-10-08
申请号：US18329467
申请日：2023-06-05
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Viswanadha Gupta Sakala , Nicholas Joseph Kray , Ambika Shivamurthy , Kirti Arvind Petkar
CPC classification number: F01D5/147 , F01D5/02 , G06F30/17 , F05D2220/32 , F05D2230/80 , F05D2240/24
Abstract: Methods, apparatus, systems and articles of manufacture corresponding to a fan blade with intrinsic damping characteristics are disclosed. An example fan blade comprises an exterior body including a first side and a second side; a first hairpin structure in contact with (a) the first side of the exterior body and (b) the second side of the exterior body; and a second hairpin structure in contact with (a) the first side and (b) the second side, wherein the first hairpin structure corresponds to a first stiffness and the second hairpin structure corresponds to a second stiffness different than the first stiffness.
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公开(公告)号：US11753942B1
公开(公告)日：2023-09-12
申请号：US17717272
申请日：2022-04-11
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Kumar Nath , Kirti Arvind Petkar , Viswanadha Gupta Sakala , Nicholas Joseph Kray
CPC classification number: F01D5/147 , F01D5/10 , F01D5/16 , F01D5/28 , F01D21/045 , F04D29/324
Abstract: An airfoil for gas turbine engines is generally provided. The airfoil defines a span extending between a root and a tip, the airfoil further defines a chord at each point along the span extending between a leading edge and a trailing edge. Further, the airfoil includes at least one frangible airfoil portion, a residual airfoil portion adjacent to the at least one frangible airfoil portion, and one or more zones. The one or more zones may include a plurality of cavities, where at least one or more cavities of the plurality of cavities include inclusions, with the inclusions having one or more materials.
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公开(公告)号：US11365636B2
公开(公告)日：2022-06-21
申请号：US16923911
申请日：2020-07-08
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Viswanadha Gupta Sakala , Nicholas Joseph Kray , Ambika Shivamurthy , Kirti Arvind Petkar
Abstract: Methods, apparatus, systems and articles of manufacture corresponding to a fan blade with intrinsic damping characteristics are disclosed. An example fan blade comprises an exterior body including a first side and a second side; a first hairpin structure coupled to the first side of the exterior body and the second side of the exterior body; and a second hairpin structure coupled to the first side and the second side, the first hairpin structure in contact with the second hairpin structure.
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公开(公告)号：US11242150B2
公开(公告)日：2022-02-08
申请号：US16015283
申请日：2018-06-22
Applicant: GENERAL ELECTRIC COMPANY
Abstract: An aircraft can include an anti-icing system. The anti-icing system can include an array of carbon nanotubes thermally coupled to at least a first exposed surface of the aircraft. The anti-icing system can also include an array of solar cells carried by the aircraft and electrically coupled to the array of carbon nanotubes.
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公开(公告)号：US11015461B2
公开(公告)日：2021-05-25
申请号：US15850842
申请日：2017-12-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Viswanadha Gupta Sakala , Douglas Duane Ward , Ming Xie
Abstract: Composite hollow blade and an associated method of forming the composite hollow blade are disclosed. The method includes forming a core by fabricating a grid core structure based on a plurality of design parameters, where the grid core includes a plurality of first reinforcing components disposed in a first curable matrix material. The method further includes forming an outer layer including a plurality of second reinforcing components disposed in a second curable matrix material. Further, the method includes coupling the core to the outer layer and curing the core and the outer layer to form the composite hollow blade.
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