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公开(公告)号：US20230126549A1
公开(公告)日：2023-04-27
申请号：US17511850
申请日：2021-10-27
Applicant: General Electric Company
Inventor： Li Zheng , Nicholas Joseph Kray , Changjie Sun
Abstract: An airfoil for a fan section of a turbine engine may include a fan blade or an outlet guide vane, and an edge guard attached thereto. The edge guard may include a heating conduit disposed within at least a portion of the edge guard. An anti-icing system for a plurality of fan blades or outlet guide vanes may include a fluid supply pathway configured to supply heating fluid to respective ones of a plurality of heating conduits within the edge guards attached to respective ones of a plurality of fan blades and/or to a plurality of outlet guide vanes. The heating fluid may include bleed air from a core air flowpath. A method of inhibiting icing on an airfoil may include flowing a heating fluid into a heating conduit disposed within an edge guard attached to the airfoil and heating the edge guard with the heating fluid.
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公开(公告)号：US11624320B2
公开(公告)日：2023-04-11
申请号：US17365855
申请日：2021-07-01
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Sreekanth Kumar Dorbala , Nitesh Jain , Prashant Sharma
Abstract: A booster splitter for a gas turbine engine and a method of additively manufacturing the booster splitter are provided. The booster splitter includes an annular inner wall defining a radially outer boundary of a compressor flow path defined through a compressor section of the gas turbine engine, an annular outer wall spaced apart from the annular inner wall along the radial direction, the annular outer wall adjacent to the annular inner wall at a forward end, the forward end defining an inlet to the compressor flow path, an annular bulkhead spanning between the annular inner wall and the annular outer wall substantially along the radial direction, the bulkhead defining an inlet port, and a passageway defined within the annular outer wall, the passageway extending from the inlet port, into the bulkhead, radially outward to the outer wall, and through the annular outer wall towards the inlet defined by the forward end.
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公开(公告)号：US20230020608A1
公开(公告)日：2023-01-19
申请号：US17375433
申请日：2021-07-14
Applicant: General Electric Company
Inventor： Nitesh Jain , Raghuveer Chinta , Nicholas Joseph Kray , Wendy Wenling Lin
IPC: F01D5/28
Abstract: A fan platform for gas turbine engine is provided. The fan platform incudes a body portion and a flow path surface coupled to the body portion. The body portion and the flow path surface define at least a portion of a flow path extending through the engine. The body portion and/or the flow path surface include an impact region including hybrid composite plies including one or more metallic tows. A gas turbine engine including the fan platform and methods for forming the fan platform are also disclosed.
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公开(公告)号：US11549391B2
公开(公告)日：2023-01-10
申请号：US17207911
申请日：2021-03-22
Applicant: General Electric Company
Inventor： Nitesh Jain , Nicholas Joseph Kray
IPC: F01D21/04
Abstract: Hybrid material components and methods of forming hybrid material components are provided. For example, a hybrid material component comprises a plurality of metallic tows and a plurality of non-metallic tows. Each metallic tow of the plurality of metallic tows is surrounded by a portion of the plurality of non-metallic tows such that the plurality of metallic tows are embedded within the plurality of non-metallic tows. An exemplary hybrid material component is a containment assembly of a gas turbine engine. Methods of forming such components include forming a hybrid material; laying up a plurality of layers of the material to form a layup; and processing the layup such that a plurality of metallic tows and a plurality of non-metallic tows are co-cured.
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75.发明申请公开(公告)号：US20220403741A1
公开(公告)日：2022-12-22
申请号：US17891312
申请日：2022-08-19
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Nitesh Jain
IPC: F01D5/02
Abstract: A rotor blade for a gas turbine engine includes an airfoil section and a root section extending along a longitudinal direction between an upstream surface and a downstream surface. The root section further extends along a radial direction between an inner surface positioned at an inner end of the root section and an outer end coupled to the airfoil section. Moreover, the root section extends along a circumferential direction between a first side surface and a second side surface. Furthermore, the root section defines a longitudinal centerline extending along the longitudinal direction and positioned equidistant from the inner surface and the outer end in the radial direction. The root section includes a first portion formed from a composite material and a second portion formed from a metallic material, with the longitudinal centerline extending through the second portion of the root section.
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Patent Agency Ranking
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：US11286795B2
公开(公告)日：2022-03-29
申请号：US16897874
申请日：2020-06-10
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray
IPC: F01D5/30 , F02C7/36 , F02C7/32 , F01D15/12 , F01D15/10 , F02C9/00 , F02C9/22 , F02K1/76 , F01D5/12 , F01D9/02 , F01D5/18 , F02C7/264 , F01D7/00 , F01D9/04 , F01D17/16 , B64C1/06 , B64D27/12 , F01D25/12 , B32B7/022 , B64C1/12 , B64D7/00 , B64C1/38 , B64C1/00
Abstract: A gas turbine engine is provided. The gas turbine engine defines a radial direction. The engine includes: an airfoil positioned within an airflow and extending between a root end and a tip along the radial direction; and a mount coupled to or formed integrally with the root end of the airfoil for mounting the airfoil to the engine, the mount including an outer surface along the radial direction exposed to the airflow and defining an air-cooling channel extending between an inlet and an outlet, the inlet positioned on the outer surface of the mount.
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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：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：US11052982B2
公开(公告)日：2021-07-06
申请号：US15295168
申请日：2016-10-17
Applicant: General Electric Company
Abstract: A blade member includes a leading edge, a trailing edge, and a blade body extending therebetween. The blade member also includes a dovetail, a transition region, and a transition relief. The dovetail includes a dovetail chord line extending between an axially forward face of the dovetail and an axially aft face of the dovetail. The dovetail chord line has a dovetail chord length. The transition region is formed between the blade body and the dovetail. The blade body and the transition region form a blade body transition chord line at the interface of the blade body and the transition region which has a blade body transition chord length. The transition relief includes a geometric relief in at least one of a forward and an aft end of the transition region and the dovetail. The dovetail chord length is less than the blade body transition chord length.
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