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    METHOD AND SYSTEM FOR INLET GUIDE VANE HEATING
    35.
    发明申请
    METHOD AND SYSTEM FOR INLET GUIDE VANE HEATING 审中-公开

    公开(公告)号：US20170175628A1

    公开(公告)日：2017-06-22

    申请号：US14971354

    申请日：2015-12-16

    Applicant: General Electric Company

    Inventor： Sesha Subramanian ,  Bhaskar Nanda Mondal ,  Sushilkumar Gulabrao Shevakari ,  Mayank Krisna Amble

    IPC: F02C7/047 ,  B64D15/04

    CPC classification number: F02C7/047 ,  F01D25/02 ,  F04D29/542 ,  F04D29/563 ,  F04D29/584 ,  F05D2240/121

    Abstract: A method of heating a hollow structure and a heating system are provided. The system includes a plurality of hollow structures spaced circumferentially about an annular flow path. The hollow structures include a heating fluid inlet port, a first plurality of film heating apertures, and a second plurality of film heating apertures. The hollow structures also include a first internal passage extending between the heating fluid inlet port and the first plurality of film heating apertures. The first internal passage includes an impingement leg configured to channel a first flow of heating fluid to a leading edge of the hollow structure. A second internal passage extends between the heating fluid inlet port and the second plurality of film heating apertures through a path along an inner surface of the hollow structure before being channeled to the second plurality of film heating apertures.

    MIDSHAFT RATING FOR TURBOMACHINE ENGINES
    37.
    发明申请
    MIDSHAFT RATING FOR TURBOMACHINE ENGINES 有权

    公开(公告)号：US20240392827A1

    公开(公告)日：2024-11-28

    申请号：US18797061

    申请日：2024-08-07

    Applicant: General Electric Company

    Inventor： Narayanan Payyoor ,  Bhaskar Nanda Mondal

    IPC: F16C3/02 ,  F02C7/06

    Abstract: A turbomachine engine including an engine core including a high-pressure compressor, which has an exit stage having an exit stage diameter (DCORE), a high-pressure turbine, and a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine, a power turbine in flow communication with the high-pressure turbine, and a low-pressure shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. The low-pressure shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). The turbomachine engine is configured to operate up to the redline speed without passing through a critical speed associated with a first-order bending mode of the low-pressure shaft. The low-pressure shaft has a length (LMSR) defined by an engine core length (LCORE) given by: L CORE = [ m   ( 20 + m ) * n   ( 10 + n ) ] ( 1 100 ) * D CORE + CIS .

    FORWARD LOAD REDUCTION STRUCTURES FOR HIGH PRESSURE COMPRESSORS
    38.
    发明申请
    FORWARD LOAD REDUCTION STRUCTURES FOR HIGH PRESSURE COMPRESSORS 有权

    公开(公告)号：US20240369072A1

    公开(公告)日：2024-11-07

    申请号：US18142745

    申请日：2023-05-03

    Applicant: General Electric Company

    Inventor： Vaishnav Raghuvaran ,  Bhaskar Nanda Mondal ,  Thomas Ory Moniz ,  Atanu Saha ,  Vaibhav Deshmukh ,  Curtis Walton Stover ,  Andrew Mark Del Donno

    IPC: F04D29/54 ,  F04D19/02 ,  F04D29/08

    Abstract: Structures for reducing forward loads in compressors are described. compressor includes inner and outer circumferential support structures positioned concentrically around a central axis, and an aft-most stage including a vane extending radially inward from the outer circumferential support structure. An axial length of the aft-most stage is defined by a spacer arm of the inner circumferential support structure. The vane includes a root, a tip, and a trailing edge extending between the root and the tip. A ratio of a first radial distance between a first point located at an intersection of the tip of the vane and the trailing edge to a radially inner wall of the spacer arm of the inner circumferential support structure to a second radial distance between the first point and a second point located at an intersection of the root of the vane and the trailing edge is between 0.95 and 4.5.

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