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    Segmented leading edge guards
    21.
    发明授权
    Segmented leading edge guards 有权

    公开(公告)号：US12044147B1

    公开(公告)日：2024-07-23

    申请号：US18176241

    申请日：2023-02-28

    Applicant: General Electric Company

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

    IPC: F01D5/28

    CPC classification number: F01D5/288 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2300/611

    Abstract: Examples disclosed herein include a fan blade of a gas turbine engine. The disclosed fan blade includes a main body having a leading edge and a trailing edge. The fan blade includes a leading edge guard covering the leading edge and a leading section of the main body adjacent to the leading edge. The leading edge guard includes a plurality of leading edge guard segments consecutively arranged in a spanwise direction along the leading edge of the fan blade. Each of the plurality of leading edge guard segments are oriented at an angle relative to a root of the fan blade. Each of the plurality of leading edge guard segments includes a nose portion coupled to the leading edge and a wing portion coupled to opposing sides of the leading section of the main body.

    APPARATUS FOR AND A METHOD OF DEICING A DUCTED FAN ENGINE
    22.
    发明公开
    APPARATUS FOR AND A METHOD OF DEICING A DUCTED FAN ENGINE 审中-公开

    公开(公告)号：US20240076059A1

    公开(公告)日：2024-03-07

    申请号：US18152906

    申请日：2023-01-11

    Applicant: General Electric Company

    Inventor： Kirti Petkar ,  Sesha Subramanian ,  Nicholas J. Kray

    IPC: B64F1/36 ,  B08B7/02 ,  B08B13/00 ,  G06T7/00

    CPC classification number: B64F1/36 ,  B08B7/026 ,  B08B13/00 ,  G06T7/0002 ,  G06T2207/10048

    Abstract: A ducted fan engine is deiced using a ground support deicing apparatus having a support structure, a plurality of sonic wave transmitters, an imaging device, and a controller that controls the sonic wave transmitters to emit sonic waves at varying frequencies. A deicing program causes the controller to control (a) providing imaging signals to obtain image data from imaging sensors, (b) receiving image data provided by each of the imaging sensors, and generates images of at least one component part of the engine, (c) detecting a presence or an absence of ice on the at least one component part of the engine, and (d) controlling the plurality of sonic wave transmitters to emit sonic waves in a given frequency range so as to remove the ice from the component part of the engine.

    Part-span shrouds for pitch controlled aircrafts
    23.
    发明授权
    Part-span shrouds for pitch controlled aircrafts 有权

    公开(公告)号：US11913355B2

    公开(公告)日：2024-02-27

    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.

    LOW RADIUS RATIO FAN BLADE FOR A GAS TURBINE ENGINE
    27.
    发明公开
    LOW RADIUS RATIO FAN BLADE FOR A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20230160312A1

    公开(公告)日：2023-05-25

    申请号：US17535291

    申请日：2021-11-24

    Applicant: General Electric Company

    Inventor： Li Zheng ,  Scott Roger Finn ,  Nicholas J. Kray ,  Trevor H. Wood ,  Kishore Ramakrishnan

    IPC: F01D5/30 ,  F01D5/28

    CPC classification number: F01D5/3007 ,  F01D5/282 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2230/60

    Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed to implement a low radius ratio fan blade for a gas turbine engine. A fan blade for a gas turbine engine includes an airfoil including a leading edge and a trailing edge extending between a root and a tip of the airfoil, a distance between the leading edge and the trailing edge defining a flow path length, a leading edge hub point defined by a radially innermost point of the leading edge, and an axial dovetail including a pair of opposed pressure faces, an axial length of the axial dovetail less than the flow path length, a top edge of the axial dovetail separating the pressure faces from the airfoil, the top edge of the axial dovetail radially outward of the leading edge hub point.

    FAN FOR A TURBINE ENGINE
    29.
    发明公开
    FAN FOR A TURBINE ENGINE 审中-公开

    公开(公告)号：US20240044253A1

    公开(公告)日：2024-02-08

    申请号：US17817511

    申请日：2022-08-04

    Applicant: General Electric Company

    Inventor： Nicholas J. Kray ,  David W. Crall ,  Anthony L. DiPietro

    IPC: F01D5/14 ,  F02K3/06

    CPC classification number: F01D5/146 ,  F02K3/06 ,  F05D2220/32 ,  F05D2240/30

    Abstract: A fan for a turbine engine having a core air flowpath and a bypass air flowpath. The fan includes a disk, a plurality of fan blades, and a plurality of splitter blades. The disk rotates about a centerline axis. The plurality of fan blades are coupled to the disk. The plurality of splitter blades are coupled to the disk and positioned between the plurality of fan blades. The plurality of splitter blades are axially aligned on the disk at a splitter blade axial distance from an annular inlet of the core air flowpath such that the plurality of splitter blades direct debris that passes through the fan into the bypass air flowpath.

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