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公开(公告)号：US11261753B2
公开(公告)日：2022-03-01
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：US20220034331A1
公开(公告)日：2022-02-03
申请号：US17502620
申请日：2021-10-15
Applicant: General Electric Company
Inventor： Nitesh Jain , Sujana Chandrasekar , Ramkrishna Maripalli , Nicholas Joseph Kray , Wendy Wenling Lin
IPC: F04D29/38 , B32B5/02 , F02C3/04 , F04D29/32 , F02K3/06 , F04D29/02 , B29C70/02 , F01D5/28 , B32B37/14 , B29C70/20
Abstract: A laminated composite airfoil assembly includes a first lamina formed of a material including metal fibers, and at least a second lamina formed of a material including at least one of metal fibers intermixed with carbon fibers, only metal fibers, only carbon fibers, a substrate including metal fibers, a substrate including carbon fibers, and combinations thereof.
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公开(公告)号：US11203934B2
公开(公告)日：2021-12-21
申请号：US16526205
申请日：2019-07-30
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Steven Mark Ballman
Abstract: A gas turbine engine defining a radial direction is provided. The gas turbine engine includes a tie shaft; a compressor section including a last rotor stage, the compressor section assembled to a first portion of the tie shaft; a separable shaft disposed between the compressor section and the tie shaft, the separable shaft having a radial outward portion and a radial inward portion, the radial outward portion of the separable shaft in contact with a portion of the last rotor stage at an interface; and a seal assembly operable with a portion of the separable shaft proximate the radial inward portion.
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公开(公告)号：US11156099B2
公开(公告)日：2021-10-26
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：US20210221491A1
公开(公告)日：2021-07-22
申请号：US17071114
申请日：2020-10-15
Applicant: General Electric Company
Abstract: In an aspect of the present disclosure, an aircraft defining a longitudinal direction and a lateral direction is provided. The aircraft includes: a fuselage; a single unducted rotor engine mounted at a location spaced from the fuselage of the aircraft, the single unducted rotor engine comprising an unducted rotor assembly having a single stage of rotor blades; and a fuselage shield attached to or formed integrally with the fuselage at a location in alignment with the single stage of rotor blades of the unducted rotor assembly along the lateral direction.
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Patent Agency Ranking
公开(公告)号：US11053848B2
公开(公告)日：2021-07-06
申请号：US15878759
申请日：2018-01-24
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 outer wall defining an internal fluid passageway in fluid communication with a fluid supply and terminating in discharge ports that eject a flow of fluid into the compressor section of the gas turbine engine. The internal fluid passageway may also be in fluid communication with heating plenums of a first plurality of airfoils for heating those airfoils.
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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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258.发明授权公开(公告)号：US10920595B2
公开(公告)日：2021-02-16
申请号：US15405656
申请日：2017-01-13
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Narendra Digamber Joshi , Nicholas Joseph Kray , Samar Jyoti Kalita , Paul Marsland , Wayne Spence
IPC: F01D5/14 , B22F5/04 , F01D9/04 , F01D25/00 , B33Y10/00 , B22F3/105 , B23K26/342 , B23K26/082 , B33Y80/00 , B23K101/00 , B23K103/18
Abstract: The present disclosure generally relates to turbine engine components having multiple controlled metallic grain orientations. In general, the primary grain orientation is aligned substantially perpendicular to the longitudinal axis of the turbine engine component while the secondary grain orientation is aligned substantially parallel to the longitudinal axis. Such controlled grain orientations provide the blades and vanes with increased strength to withstand the thermal-mechanical stresses of the turbine operation. The disclosure also relates to turbines having these fortified components, and methods of manufacturing the components.
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公开(公告)号：US10815795B2
公开(公告)日：2020-10-27
申请号：US16226756
申请日：2018-12-20
Applicant: General Electric Company
Abstract: A blade for a propulsion apparatus that includes a body formed of a first material. The body includes opposed pressure and suction sides and extends in span between a root and a tip. The body extends in court between a leading edge and a trailing edge. A tension element is positioned within the body and extends between the root and the tip. The tension element includes at least one string that is configured to be under tension such that at least a portion of the blade between the root and the tip is under compression.
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公开(公告)号：US20200318486A1
公开(公告)日：2020-10-08
申请号：US16375179
申请日：2019-04-04
Applicant: General Electric Company
Inventor： Gregory Carl Gemeinhardt , Nicholas Joseph Kray , Andreas Mastorakis
Abstract: A component for a gas turbine engine. The component includes a continuous fiber blade including an airfoil extending radially between a root and a tip and a blade attachment feature positioned at or adjacent to the root. The component further includes a platform coupled to the root of the continuous fiber blade. The platform includes a plurality of chopped fibers. Additionally, the component includes a thermoplastic polymer contained in both the continuous fiber blade and the platform. Moreover, the continuous fiber blade and platform are coupled together such that the continuous fiber blade and platform form a monolithic composite body.
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