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公开(公告)号：US20230008935A1
公开(公告)日：2023-01-12
申请号：US17408986
申请日：2021-08-23
Applicant: General Electric Company
Inventor： Abhijeet Jayshingrao Yadav , Nitesh Jain , Nicholas Joseph Kray , Ravindra Shankar Ganiger , Praveen Sharma
Abstract: An airfoil arrangement for a gas turbine engine may include a clearance device using a shape memory alloy movable to provide clearance between an airfoil and one or more other components of the gas turbine engine. The clearance device may be formed as part of a fan blade. The arrangement may be configured to reduce overall weight and dimensions of the gas turbine engine.
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公开(公告)号：US20230003132A1
公开(公告)日：2023-01-05
申请号：US17366525
申请日：2021-07-02
Applicant: General Electric Company
Abstract: An airfoil including a plurality of composite plies extending from a leading edge to a trailing edge and between a tip and a root. The airfoil further includes a frangible airfoil portion at the tip extending between the leading edge and the trailing edge and extending between the tip and a frangible line along a span including a first plurality of composite plies. The frangible airfoil portion includes a first plurality of composite plies including fibers having a first fiber modulus. The airfoil further includes a residual airfoil portion extending from the frangible line to the root along the span including a second plurality of composite plies. The second plurality of composite plies including one or more plies having a second fiber modulus. The second fiber modulus is greater than the first fiber modulus. Further, the residual airfoil portion meets the frangible airfoil portion at the frangible line.
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公开(公告)号：US20230003129A1
公开(公告)日：2023-01-05
申请号：US17363102
申请日：2021-06-30
Applicant: General Electric Company
Inventor： Nitesh Jain , Nicholas Joseph Kray , Daniel Edward Mollmann , David William Crall
Abstract: Composite airfoils and methods for forming composite airfoils are provided. For example, a composite airfoil of a gas turbine engine comprises opposite pressure and suction sides extending radially along a span from a root to a tip, which define opposite radial extremities of the airfoil. The composite airfoil further comprises a body section and a tip section, which includes the tip, that each extend radially along the span. The composite airfoil is formed from a composite material comprising fibers disposed in a matrix material. The tip section has a tip fiber volume, and the body section has a body fiber volume that is greater than the tip fiber volume. Another composite airfoil comprises a tip cap applied over the tip that tapers from a first end to a second end such that each of the pressure and suction side walls of the tip cap narrows from a first thickness to a second thickness.
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公开(公告)号：US11519278B2
公开(公告)日：2022-12-06
申请号：US17193064
申请日：2021-03-05
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Elzbieta Kryj-Kos
Abstract: A rotor blade retention system for a gas turbine engine includes a rotor blade connection component defining a slot, with the rotor blade connection component including a first set of electric leads. Furthermore, the rotor blade retention system includes a rotor blade having a root section received within the slot, with the rotor blade further including a second set of electric leads. In this respect, the first and second sets of electric leads are electrically coupled together to permit electric current to be supplied to the rotor blade.
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公开(公告)号：US20220333492A1
公开(公告)日：2022-10-20
申请号：US17232822
申请日：2021-04-16
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Nitesh Jain
Abstract: In one exemplary embodiment of the present disclosure an airfoil is provided. The airfoil defines a spanwise direction, a root end, and a tip end. The airfoil includes: a body defining a pressure side and a suction side and extending along the spanwise direction between the root end and the tip end, the body formed of a composite material; and a spar enclosed in the body of the airfoil extending along the spanwise direction, the spar comprising a plurality of spar segments arranged in an overlapping configuration along the spanwise direction.
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Patent Agency Ranking
公开(公告)号：US20220307388A1
公开(公告)日：2022-09-29
申请号：US17210845
申请日：2021-03-24
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Nitesh Jain
Abstract: Hybrid composite components, such as gas turbine engine containment assemblies, and methods of forming such components are provided. For example, a hybrid composite component comprises an annular composite shell and an annular metallic shell joined with the composite shell. At least one segment of the metallic shell interlocks with the composite shell or another segment of the metallic shell along an axial length. An exemplary containment assembly comprises a containment case extending along an axial direction about a longitudinal centerline of the gas turbine engine. The containment case has an inner surface and an outer surface spaced apart along a radial direction and includes an annular composite shell joined with an annular metallic shell. The metallic shell defines a first portion of the inner surface and the composite shell defines a second portion of the inner surface.
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137.发明授权公开(公告)号：US11454118B2
公开(公告)日：2022-09-27
申请号：US17012595
申请日：2020-09-04
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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公开(公告)号：US11434781B2
公开(公告)日：2022-09-06
申请号：US16161233
申请日：2018-10-16
Applicant: General Electric Company
Inventor： Nitesh Jain , David William Crall , Nicholas Joseph Kray , Daniel Edward Mollmann
Abstract: An airfoil defining a span extending between a root and a tip. The airfoil includes a frangible airfoil portion extending between a leading edge and a trailing edge and extending between the tip and a fusion line along the span. The frangible airfoil portion includes a first material defining a first modulus of elasticity and further defines an internal cavity. The airfoil includes a residual airfoil portion coupled to the frangible airfoil portion extending from the fusion line to the root along the span and including a second material defining a second modulus of elasticity greater than the first modulus of elasticity. The residual airfoil portion meets the frangible airfoil portion at the fusion line.
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公开(公告)号：US11428112B2
公开(公告)日：2022-08-30
申请号：US17063266
申请日：2020-10-05
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. An example casing includes an outer layer material, an inner layer material including first openings extended partially through the inner layer material along a radial direction of a first side of the inner layer material, and second openings extended partially through the inner layer material along the radial direction of a second side of the inner layer material opposite the first side, and a spring member coupled to the outer layer material and the inner layer material.
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公开(公告)号：US20220082022A1
公开(公告)日：2022-03-17
申请号：US17024212
申请日：2020-09-17
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Nitesh Jain
IPC: F01D5/08
Abstract: A rotor disk for a gas turbine engine includes a disk body having a central bore extending therethrough. The disk body includes a bore body that extends around the central bore, a web that extends radially outward from the bore body having decreased thickness relative to the bore body and a peripheral rim that is located at an outer end of the web. The peripheral rim includes blade mounting structures for engaging complimentary mounting structures of rotor blades. The bore body has a bore cavity that extends continuously through the bore body and about an entire periphery of the central bore. The bore cavity has a central axis that forms a circle about the central bore.
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