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    PART-SPAN SHROUDS FOR PITCH CONTROLLED AIRCRAFTS
    24.
    发明公开
    PART-SPAN SHROUDS FOR PITCH CONTROLLED AIRCRAFTS 审中-公开

    公开(公告)号：US20230258092A1

    公开(公告)日：2023-08-17

    申请号：US17947589

    申请日：2022-09-19

    Applicant: General Electric Company

    Inventor： Nicholas J. Kray ,  Nitesh Jain ,  Gary W. Bryant

    IPC: F01D5/22 ,  F01D5/16

    CPC classification number: F01D5/225 ,  F01D5/16

    Abstract: Part-span shrouds for pitch controlled aircrafts are disclosed herein. An example apparatus includes a first portion extending from a first airfoil, the first portion including a first surface, the first surface being convex, a second portion extending from a second airfoil towards the first airfoil, the second portion including a second surface the first airfoil circumferentially adjacent to the second airfoil, the second surface being concave, and an interface formed by the first surface and the second surface, the interface reacting circumferential loads between the first airfoil and the second airfoil.

    Additively manufactured booster splitter with integral heating passageways
    25.
    发明授权
    Additively manufactured booster splitter with integral heating passageways 有权

    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

    IPC: F02C7/047 ,  B64D33/02 ,  F01D25/02

    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.

    GAS TURBINE ENGINE FAN PLATFORM
    26.
    发明申请
    GAS TURBINE ENGINE FAN PLATFORM 有权

    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.

    Component formed from hybrid material
    27.
    发明授权
    Component formed from hybrid material 有权

    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.

    GAS TURBINE ENGINE ROTOR BLADE HAVING A ROOT SECTION WITH COMPOSITE AND METALLIC PORTIONS
    28.
    发明申请
    GAS TURBINE ENGINE ROTOR BLADE HAVING A ROOT SECTION WITH COMPOSITE AND METALLIC PORTIONS 有权

    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.

    AIRFRAME LOCALIZED KEEL STRUCTURES
    30.
    发明申请
    AIRFRAME LOCALIZED KEEL STRUCTURES 有权

    公开(公告)号：US20220212772A1

    公开(公告)日：2022-07-07

    申请号：US17141899

    申请日：2021-01-05

    Applicant: General Electric Company

    Inventor： Nicholas J. Kray ,  Nitesh Jain ,  Abhijeet Jayshingrao Yadav

    IPC: B64C1/06 ,  B64C5/06 ,  B64D27/02

    Abstract: Airframe localized keel structures are disclosed. An example aircraft includes an airframe, a first engine mounted on a first side of the airframe, a second engine mounted on a second side of the airframe, and an airframe keel positioned on at least one of a lower portion of the airframe or an upper portion of the airframe between the first engine and the second engine, the airframe keel to prevent an object from exiting the first engine and impacting the second engine.

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