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    TURBINE ENGINE INCLUDING A STEAM SYSTEM
    2.
    发明申请
    TURBINE ENGINE INCLUDING A STEAM SYSTEM 有权

    公开(公告)号：US20250084789A1

    公开(公告)日：2025-03-13

    申请号：US18463782

    申请日：2023-09-08

    Applicant: General Electric Company

    Inventor： Arthur W. Sibbach ,  Aaron M. Dziech ,  Scott Alan Schimmels ,  Robert R. Rachedi ,  Jeffrey D. Rambo ,  Brandon W. Miller

    IPC: F02C6/18 ,  B64D27/10 ,  F01K23/10

    Abstract: A turbine engine for an aircraft. The turbine engine includes a combustor fluidly coupled to a fuel delivery assembly to receive fuel from the fuel delivery assembly. The fuel is injected into the combustor and combusted in the combustor to generate combustion gases. A condenser is located downstream of a turbine to receive the combustion gases and to condense water. The fuel heat exchanger is thermally coupled to the condenser to receive heat from the water condensed by the condenser. The fuel heat exchanger is located in the fuel delivery assembly to receive the fuel and to transfer the heat received from the water to the fuel. The boiler is located downstream of the fuel heat exchanger. The boiler receives the water and is fluidly connected to the combustor to receive the combustion gases and to boil the water to generate steam.

    Aircraft gas turbine engine with heated fuel to assist combustion
    3.
    发明授权
    Aircraft gas turbine engine with heated fuel to assist combustion 有权

    公开(公告)号：US12240624B1

    公开(公告)日：2025-03-04

    申请号：US18461651

    申请日：2023-09-06

    Applicant: General Electric Company

    Inventor： Brandon W. Miller ,  Daniel A. Niergarth ,  Arthur W. Sibbach

    IPC: F02C7/224 ,  B64D37/34 ,  F02C7/262 ,  F02C9/28

    Abstract: An aircraft gas turbine includes a combustor that combusts compressed air and at least one fuel flow from at least one fuel source to generate combustion gases. A fuel supply system is arranged to provide at least one of a first flow of fuel to the combustor via a first fuel supply line and a second flow of a heated fuel to the combustor via a second fuel supply line. A fuel heat exchanger is arranged within the fuel supply system to generate the heated fuel that is heated above an autoignition temperature of the fuel, and a heat source communicates with the fuel heat exchanger for generating the heated fuel.

    METHODS AND APPARATUS TO DETERMINE ENGINE STATUS WITH PLENUM MEASUREMENTS
    4.
    发明申请
    METHODS AND APPARATUS TO DETERMINE ENGINE STATUS WITH PLENUM MEASUREMENTS 有权

    公开(公告)号：US20240402047A1

    公开(公告)日：2024-12-05

    申请号：US18329150

    申请日：2023-06-05

    Applicant: General Electric Company

    Inventor： Brandon W. Miller ,  Andrew J. Hank ,  John C. Schilling ,  Ryan T. Roehm ,  Kevin Graziano ,  Geoffrey Whitener

    IPC: G01M15/14 ,  F01D21/00

    Abstract: A disclosed example non-transitory machine readable storage medium includes instructions to cause programmable circuitry to at least determine, based on output from at least one sensor, (i) a first parameter corresponding to a first position in a casing of a gas turbine engine, the first position at or downstream of a volume at which flows from respective ones of bleed offtakes are combined, and (ii) a second parameter corresponding to a second position in a casing of a gas turbine engine, the second position upstream from the first position, determine a status of at least one of the bleed offtakes or the at least one sensor based on the first and second parameters, and provide or indicate the status in response to the status indicating improper operation of at least one of the bleed offtakes or the at least one sensor.

    Midshaft rating for turbomachine engines
    5.
    发明授权
    Midshaft rating for turbomachine engines 有权

    公开(公告)号：US12140081B2

    公开(公告)日：2024-11-12

    申请号：US18481597

    申请日：2023-10-05

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

    Inventor： Narayanan Payyoor ,  Weize Kang ,  Brandon W. Miller ,  Bugra H. Ertas ,  Andrea Piazza

    IPC: F02C7/36 ,  F02C7/06

    Abstract: A turbomachine engine includes a fan section having a fan shaft, and a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine includes a low-speed shaft coupled to the power turbine and having a midshaft that extends from a forward bearing to an aft bearing. The low-speed shaft is characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. The low-speed shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). The turbomachine engine includes a gearbox assembly that couples the fan shaft to the low-speed shaft and characterized by a gearbox assembly mode less than 95% of a midshaft mode of the midshaft or greater than 105% of the midshaft mode.

    GAS TURBINE ENGINE WITH THIRD STREAM
    10.
    发明申请
    GAS TURBINE ENGINE WITH THIRD STREAM 有权

    公开(公告)号：US20250122849A1

    公开(公告)日：2025-04-17

    申请号：US18991142

    申请日：2024-12-20

    Applicant: General Electric Company

    Inventor： Brandon W. Miller ,  Randy M. Vondrell ,  David M. Ostdiek ,  Craig W. Higgins ,  Alexander Simpson ,  William Bowden

    IPC: F02K3/065 ,  F02C3/06

    Abstract: A gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct; a primary fan driven by the turbomachine; and a secondary fan located downstream of the primary fan within the inlet duct. The gas turbine engine defines a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10. The thrust to power airflow ratio is a ratio of airflow through a bypass passage over the turbomachine plus airflow through the fan duct to airflow through the core duct. The core bypass ratio is a ratio of airflow through the fan duct to airflow through the core duct. The fan duct includes an exhaust nozzle having a plurality of chevrons disposed at its aft end to define an exhaust outlet.

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