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    GAS TURBINE ENGINE
    1.
    发明申请
    GAS TURBINE ENGINE 有权

    公开(公告)号：US20250101919A1

    公开(公告)日：2025-03-27

    申请号：US18976748

    申请日：2024-12-11

    Applicant: General Electric Company ,  GE Avio S.r.l.

    Inventor： Daniel Alan Niergarth ,  Jorge de Luis ,  Douglas Downey Turner ,  Michael Macrorie ,  Keith W. Wilkinson ,  Arthur William Sibbach ,  Vincenzo Martina

    IPC: F02C6/06 ,  F02C7/18

    Abstract: A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows: ( T OUT A DTExit ) 2 * EGT A HPCExit * 1 ⁢ 0 - 1 ⁢ 1 ; wherein CSP is greater than 0.0001194×EGT2−0.103×EGT+22.14 and less than 0.0003294×EGT2−0.306×EGT+77.91; and wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.

    GAS TURBINE ENGINE
    2.
    发明公开
    GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20240280049A1

    公开(公告)日：2024-08-22

    申请号：US18650586

    申请日：2024-04-30

    Applicant: General Electric Company ,  GE Avio S.r.l.

    Inventor： Daniel Alan Niergarth ,  Jorge de Luis ,  Douglas Downey Turner ,  Michael Macrorie ,  Keith W. Wilkinson ,  Arthur William Sibbach ,  Vincenzo Martina

    IPC: F02C6/06 ,  F02C7/18

    CPC classification number: F02C6/06 ,  F02C7/185 ,  F05D2260/213

    Abstract: A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows:







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    wherein CSP is greater than 0.0001194×EGT2−0.103×EGT+22.14 and less than 0.0003294×EGT2−0.306×EGT+77.91; and wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.

    Core air leakage redirection structures for aircraft engines
    5.
    发明授权
    Core air leakage redirection structures for aircraft engines 有权

    公开(公告)号：US12134974B2

    公开(公告)日：2024-11-05

    申请号：US17880832

    申请日：2022-08-04

    Applicant: General Electric Company

    Inventor： Ya-Tien Chiu ,  Giridhar Jothiprasad ,  David V. Parker ,  Michael Macrorie

    IPC: F01D9/04

    Abstract: A stator structure including a plurality of stator blades and redirection structures including a first portion and a second portion, the first portion disposed on a front edge surface of a stator hub and a second portion disposed on a facing of the stator hub is provided. The stator hub includes the facing and the front edge surface, the facing being disposed generally perpendicular to the casing, and the front edge surface is disposed generally perpendicular to the facing. During operation of a turbine engine a core air flow moves along the longitudinal axis and past the plurality of stator blades, and a leakage air flow moves in a direction different to the core air flow, the redirection structures are effective to redirect the leakage air flow to merge into the core air flow.

    Centrifugal compressor curved diffusing passage portion
    7.
    发明授权
    Centrifugal compressor curved diffusing passage portion 有权

    公开(公告)号：US10422345B2

    公开(公告)日：2019-09-24

    申请号：US15101633

    申请日：2014-10-17

    Applicant: General Electric Company

    Inventor： David Vickery Parker ,  Michael Macrorie ,  Caitlin Jeanne Smythe ,  David Paul Miller

    IPC: F04D29/44 ,  F01D9/02 ,  F04D17/10

    Abstract: A diffuser for a centrifugal compressor including an annular diffuser housing having a plurality of diffuser flow passages therethrough the housing. Each passage including a throat portion and a diffusing section with upstream and downstream diffusing portions. A diffusing passage centerline includes a linear portion extending downstream through the throat portion and the upstream diffusing portion and a curved portion of the diffusing passage centerline extending downstream from the centerline linear portion through the downstream diffusing portion. The diffuser flow passages may have an equivalent cone angle varying non-linearly or more particularly curvilinearly downstream along curved portion. The downstream diffusing portion may be flared.

    Gas turbine engine
    9.
    发明授权
    Gas turbine engine 有权

    公开(公告)号：US12196131B2

    公开(公告)日：2025-01-14

    申请号：US18650586

    申请日：2024-04-30

    Applicant: General Electric Company ,  GE Avio S.r.l.

    Inventor： Daniel Alan Niergarth ,  Jorge de Luis ,  Douglas Downey Turner ,  Michael Macrorie ,  Keith W. Wilkinson ,  Arthur William Sibbach ,  Vincenzo Martina

    IPC: F02C7/18 ,  F02C6/06

    Abstract: A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows: ( T O ⁢ U ⁢ T A D ⁢ T ⁢ E ⁢ x ⁢ i ⁢ t ) 2 * E ⁢ G ⁢ T A H ⁢ P ⁢ C ⁢ E ⁢ x ⁢ i ⁢ t * 1 ⁢ 0 - 1 ⁢ 1 ; wherein CSP is greater than 0.0001194×EGT2−0.103×EGT+22.14 and less than 0.0003294×EGT2−0.306×EGT+77.91; and wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.

    Core Air Leakage Redirection Structures for Aircraft Engines
    10.
    发明公开
    Core Air Leakage Redirection Structures for Aircraft Engines 审中-公开

    公开(公告)号：US20240044257A1

    公开(公告)日：2024-02-08

    申请号：US17880832

    申请日：2022-08-04

    Applicant: General Electric Company

    Inventor： Ya-tien Chiu ,  Giridhar Jothiprasad ,  David V. Parker ,  Michael Macrorie

    IPC: F01D9/04

    CPC classification number: F01D9/041 ,  F05D2240/12 ,  F05D2220/3216 ,  F05D2230/237

    Abstract: A stator structure including a plurality of stator blades and redirection structures including a first portion and a second portion, the first portion disposed on a front edge surface of a stator hub and a second portion disposed on a facing of the stator hub is provided. The stator hub includes the facing and the front edge surface, the facing being disposed generally perpendicular to the casing, and the front edge surface is disposed generally perpendicular to the facing. During operation of a turbine engine a core air flow moves along the longitudinal axis and past the plurality of stator blades, and a leakage air flow moves in a direction different to the core air flow, the redirection structures are effective to redirect the leakage air flow to merge into the core air flow.

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