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135 条记录 (耗时 0.023 秒)

    PROPELLER CONTROL UNIT
    51.
    发明申请
    PROPELLER CONTROL UNIT 有权

    公开(公告)号：US20220243606A1

    公开(公告)日：2022-08-04

    申请号：US17165108

    申请日：2021-02-02

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： Jagoda KRZYWON

    IPC分类号： F01D15/02 ,  F01D7/00 ,  F01D15/12

    摘要： A propeller control unit (PCU) for controlling pitch angles of blades of a propeller, has: a pitch angle actuator; a servo valve hydraulically connected to the pitch angle actuator and to a first hydraulic fluid source; and a feather valve having a body movable within a cavity, the feather valve having a first actuation port and a second actuation port both in fluid communication with the cavity, the body between the first actuation port and the second actuation port, the body being movable to selectively hydraulically connect the pitch angle actuator to the servo valve through the feather valve or to hydraulically connect the pitch angle actuator to a drain line through the feather valve, the first actuation port and the second actuation port hydraulically connected to a second hydraulic fluid source independent from the first hydraulic fluid source.

    COMBUSTION LINER AND GAS TURBINE ENGINE COMPRISING A COMBUSTION LINER
    52.
    发明申请
    COMBUSTION LINER AND GAS TURBINE ENGINE COMPRISING A COMBUSTION LINER 审中-公开

    公开(公告)号：US20200277868A1

    公开(公告)日：2020-09-03

    申请号：US16786037

    申请日：2020-02-10

    申请人： ROLLS-ROYCE plc

    发明人： Paul A. HUCKER ,  Stephen C. HARDING ,  Quentin BORLON

    IPC分类号： F01D9/02 ,  F01D15/02 ,  F23R3/42

    摘要： A combustion liner for a gas turbine engine. The combustion liner defines a bypass direction which extends between an upstream portion and a downstream portion of the combustion liner in use, the combustion liner. The combustion liner comprises a liner wall for defining at least a portion of a combustion chamber, the liner wall having an outer surface and an inner surface and a depth between the outer and inner surfaces of the combustion liner in use. The combustion liner comprises a chute formed through the liner wall for conveying fluid from the outer surface through the liner wall and ejecting fluid from an exhaust hole of the chute on the inner surface, the exhaust hole having a length L along the bypass direction. The combustion liner also comprises a fluid-guiding surface at an upstream side of the chute which defines an arc terminating at the exhaust hole, the fluid guiding surface configured to guide fluid from a direction generally parallel to the outer surface into the chute to be ejected from the chute exhaust hole at a direction generally perpendicular to the inner surface.

    LOW PRESSURE COMPRESSOR CONTROL FOR A GAS TURBINE ENGINE
    53.
    发明申请
    LOW PRESSURE COMPRESSOR CONTROL FOR A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20200182158A1

    公开(公告)日：2020-06-11

    申请号：US16656206

    申请日：2019-10-17

    申请人： UNITED TECHNOLOGIES CORPORATION

    发明人： Daniel Bernard Kupratis

    IPC分类号： F02C7/36 ,  F01D15/10 ,  F01D15/02 ,  B64D27/24

    摘要： A gas turbine engine includes a low speed spool mechanically interconnecting a low pressure turbine and at least one of a fan and a prop, a high speed spool mechanically interconnecting a high pressure turbine and a high pressure compressor, and an epicyclic gear system mechanically coupled to the high speed spool. The gas turbine engine also includes a low pressure compressor mechanically coupled to the high speed spool via the epicyclic gear system. The low pressure compressor may be mechanically independent of the low speed spool. The gas turbine engine may include a plurality of motor-generators for transferring power between the high speed spool and the low pressure compressor.

    DUCTED FAN PROPULSION ENGINE
    55.
    发明申请
    DUCTED FAN PROPULSION ENGINE 审中-公开

    公开(公告)号：US20180201369A1

    公开(公告)日：2018-07-19

    申请号：US15603195

    申请日：2017-05-23

    申请人： MICHAEL JOHNSON

    发明人： MICHAEL JOHNSON

    IPC分类号： B64C29/00 ,  F01D15/02 ,  B64C1/16 ,  B64C3/32

    CPC分类号： B64C29/0033 ,  B64C11/001

    摘要： A propulsion engine for an aircraft comprises an enclosure having a longitudinal axis oriented in a direction of travel of an aircraft, the enclosure including a series of walls and a plurality of ducts arranged along the longitudinal axis. Each of the ducts including a number of walls that are either dynamic or static in movement. Each of the ducts includes a central axis that is angled at, or can be adjusted to, an angle toward the front wall of the enclosure such that a top end of each duct is toward the front wall of the enclosure. A fan is disposed in each of the ducts configured to generate airflow along the respective central axes from the top end to the bottom end to provide lift and thrust to the aircraft.

    System for converting gaseous fuel into liquid fuel
    59.
    发明授权
    System for converting gaseous fuel into liquid fuel 有权
    将气体燃料转化为液体燃料的系统

    公开(公告)号：US09309810B2

    公开(公告)日：2016-04-12

    申请号：US13715536

    申请日：2012-12-14

    申请人： Electro-Motive Diesel, Inc.

    发明人： Aaron Foege

    IPC分类号： F02C7/22 ,  F25J1/00 ,  F25J1/02 ,  F02C6/20 ,  F01D15/00 ,  F01D15/02 ,  F02C6/06 ,  C10G5/06

    CPC分类号： F02C7/22 ,  C10G5/06 ,  F01D15/005 ,  F01D15/02 ,  F02C6/06 ,  F02C6/20 ,  F25J1/0022 ,  F25J1/005 ,  F25J1/007 ,  F25J1/0204 ,  F25J1/0221 ,  F25J1/023 ,  F25J1/0251 ,  F25J1/0275 ,  F25J1/0283 ,  F25J2210/40 ,  F25J2230/22 ,  F25J2230/30 ,  F25J2240/10 ,  F25J2240/80 ,  F25J2270/14

    摘要： A system for converting gaseous fuel into liquid fuel is provided. The system may have a combustor configured to receive a supply of gaseous fuel. The system may also have a gas compressor configured to direct gaseous fuel from the supply into the combustor. The system may also have an air compressor configured to direct compressed air into the combustor, and a turbine in fluid communication with an outlet of the combustor. The turbine may be connected to drive the gas compressor and the air compressor. The system may also have at least one heat exchanger in fluid communication with an outlet of the gas compressor and an outlet of the air compressor. The system may also have at least one expander in fluid communication with an outlet of the at least one heat exchanger. The system may also have a condenser in fluid communication with an outlet of the at least one expander.

    摘要翻译： 提供了一种将气态燃料转化为液体燃料的系统。 该系统可以具有构造成接收气体燃料供应的燃烧器。 该系统还可以具有气态压缩机，该气体压缩机构造成将气态燃料从供给管引入燃烧器。 该系统还可以具有被配置为将压缩空气引导到燃烧器中的空气压缩机，以及与燃烧器的出口流体连通的涡轮机。 涡轮机可以连接以驱动气体压缩机和空气压缩机。 该系统还可以具有与气体压缩机的出口和空气压缩机的出口流体连通的至少一个热交换器。 该系统还可以具有与至少一个热交换器的出口流体连通的至少一个膨胀器。 该系统还可以具有与至少一个膨胀机的出口流体连通的冷凝器。