中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

416 records (took 0.026 seconds)

    DRIVE SYSTEM, AND AIRCRAFT INCLUDING A DRIVE SYSTEM
    72.
    发明公开
    DRIVE SYSTEM, AND AIRCRAFT INCLUDING A DRIVE SYSTEM 审中-公开

    公开(公告)号：US20240263579A1

    公开(公告)日：2024-08-08

    申请号：US18639770

    申请日：2024-04-18

    Applicant: MTU Aero Engines AG

    Inventor： Istvan BOLGAR ,  Alexander WOITALKA

    IPC: F02C3/34 ,  F02C7/141

    CPC classification number: F02C3/34 ,  F02C7/141

    Abstract: A drive system (10) including a gas turbine (1), designed in particular as an aircraft engine. The gas turbine (1) includes a core flow channel (1c) in which at least one compressor (2), in particular a mixing chamber (3a), a combustion chamber (3), and a turbine (4), are situated in the flow direction, and a steam system (20) for separating water from an exhaust gas stream of the core flow channel (1c), for generating steam, and for conveying the steam, in particular across the mixing chamber (3a) into the combustion chamber (3). A drive system (10) whose efficiency is increased is provided in that the steam system (20) is coupled to a separate cooling system (30) in order to contribute to the separation of the water for generating the steam from an exhaust gas stream of the core flow channel (1c), via absorption and discharge of heat.

    Gas turbine engine
    74.
    发明授权
    Gas turbine engine 有权

    公开(公告)号：US11879413B2

    公开(公告)日：2024-01-23

    申请号：US17940480

    申请日：2022-09-08

    Applicant: ROLLS-ROYCE plc

    Inventor： Paul R Davies ,  Gareth E Moore ,  Stephen M Husband ,  David R Trainer ,  David P Scothern ,  Luke George

    IPC: F02K3/06 ,  F01D15/10 ,  F02C7/141

    CPC classification number: F02K3/06 ,  F01D15/10 ,  F02C7/141 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2260/213 ,  F05D2260/606

    Abstract: An aircraft gas turbine engine includes a heat exchanger module, and a core engine. The core engine includes an intermediate-pressure compressor, high-pressure compressor, and high and low-pressure turbines. The high-pressure compressor rotationally connects to the high-pressure turbine by a first shaft, and the intermediate-pressure compressor rotationally connects to the low-pressure turbine by a second shaft. The heat exchanger module fluidly communicates with the core engine by an inlet duct. The heat exchanger module includes a central hub and multiple heat transfer elements extending radially from the hub and spaced in a circumferential array, for heat energy transfer from a first fluid within the elements to an inlet airflow passing over a surface of the elements prior to airflow entry into an inlet to the core engine. The gas turbine engine further includes a first electric machine rotationally connected to the first shaft, and positioned downstream of the heat exchanger module.

    Contrail suppression system
    76.
    发明授权
    Contrail suppression system 有权

    公开(公告)号：US11815030B1

    公开(公告)日：2023-11-14

    申请号：US17860445

    申请日：2022-07-08

    Applicant: General Electric Company

    Inventor： Eyitayo James Owoeye

    IPC: F02C9/18 ,  F02C7/141

    CPC classification number: F02C9/18 ,  F02C7/141 ,  F05D2220/323 ,  F05D2270/081

    Abstract: A contrail suppression system includes a shell having an exhaust gas inlet, an exhaust gas outlet, a condensate drain and a flow chamber in fluid communication with the exhaust gas inlet, the exhaust gas outlet and the condensate drain. The exhaust gas inlet is in fluid communication with a jet exhaust nozzle of a gas turbine engine. A first tube bundle is disposed within the flow chamber downstream from the exhaust gas inlet. The first tube bundle includes an inlet and an outlet. The inlet of the first tube bundle is fluidly connected to a first cooling medium source. A second tube bundle is disposed within the flow chamber downstream from the first tube bundle and upstream from the exhaust gas outlet. The second tube bundle includes an inlet and an outlet. The inlet of the second tube bundle is fluidly connected to a second cooling medium source.

    TURBORAMJET ENGINE
    77.
    发明公开
    TURBORAMJET ENGINE 审中-公开

    公开(公告)号：US20230340930A1

    公开(公告)日：2023-10-26

    申请号：US18025373

    申请日：2021-09-08

    Applicant: Pradeep DASS

    Inventor： Pradeep DASS

    IPC: F02K7/16 ,  F02C7/141 ,  F02C9/18

    CPC classification number: F02K7/16 ,  F02C7/141 ,  F02C9/18 ,  F05D2260/213 ,  F05D2220/10 ,  F05D2300/133 ,  F05D2300/125

    Abstract: A turboramjet has a housing with an intake and an exhaust. The housing houses a heat exchanger, a turbojet section and a ramjet section downstream of the turbojet section. The heat exchanger has an air path and a coolant path. The air path is configured to receive air from the air intake. The heat exchanger has a first section made from a first material and a second section made from a second material, the second material having a lower melting point and a lower density relative to the first material. A bypass air passage selectively bypasses the turbojet section to supply air to the ramjet section, and the coolant path uses fuel as a coolant and is configured to supply the fuel to the turbojet section.

Patent Agency Ranking