知搜-全球专利检索

  1. 登录
  2. 注册

搜索结果

5 条记录 (耗时 0.014 秒)

    TURBINE-TIP CLEARANCE CONTROL SYSTEM OFFTAKE
    1.
    发明申请
    TURBINE-TIP CLEARANCE CONTROL SYSTEM OFFTAKE 审中-公开

    公开(公告)号：US20200056496A1

    公开(公告)日：2020-02-20

    申请号：US16526508

    申请日：2019-07-30

    申请人： ROLLS-ROYCE plc

    发明人： Clare L. BEWICK ,  Robert GOULDS

    IPC分类号： F01D11/24

    摘要： A turbine-tip clearance control system offtake for a gas turbine engine, comprising: an air input duct in fluid communication with a compressor bleed air outlet, the air input duct comprising an exit aperture, the exit aperture defining an exit flow path for at least a portion of the air flowing in the air input duct during use of the gas turbine engine. The direction of airflow through the exit aperture, during use of the gas turbine engine, has at least a component that is anti-parallel to the direction of airflow in the air input duct in a region of the air input duct adjacent to the exit aperture. A turbine-tip clearance control system, a gas turbine engine for an aircraft and a method of supplying airflow to a turbine-tip clearance control system in a gas turbine engine are also disclosed.

    GAS TURBINE ENGINE
    2.
    发明申请
    GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20190323433A1

    公开(公告)日：2019-10-24

    申请号：US16379915

    申请日：2019-04-10

    申请人： ROLLS-ROYCE plc

    发明人： Clare L. BEWICK ,  Zahid M. HUSSAIN ,  David P. SCOTHERN ,  John R. MASON

    IPC分类号： F02C7/18 ,  F02C3/06

    摘要： A gas turbine engine (10) comprising: an engine core (11), comprising a compressor (14, 15); an outer casing (25A) separating the engine core (11) from a bypass airflow; a compressor bleed valve (50) in communication with the compressor (14, 15) and configured to release bleed air from the compressor (14, 15); a bleed air duct (51) connected to the compressor bleed valve (50) and configured to eject the bleed air released by the compressor bleed valve (50) into an airflow at a location radially inward of the outer casing (25A).

    ACCESSORY GEARBOX ASSEMBLY
    3.
    发明申请
    ACCESSORY GEARBOX ASSEMBLY 审中-公开

    公开(公告)号：US20200325827A1

    公开(公告)日：2020-10-15

    申请号：US16835674

    申请日：2020-03-31

    申请人： ROLLS-ROYCE plc

    发明人： Clare L. BEWICK ,  David A. EDWARDS

    IPC分类号： F02C7/32 ,  F02C7/22

    摘要： The disclosure relates to a gas turbine engine (10) having an accessory gearbox assembly having an accessory gearbox (42). The accessory gearbox assembly is mounted adjacent a core (11) of the gas turbine engine (10) and has a support formation for supporting a conduit (50). The conduit (50) extends between a first location (52) on the engine (10) and a second location (54) on the engine (10). The first location (52) and the second location (54) may be spaced from the accessory gearbox (42) such that the conduit (50) does not operatively communicate with the accessory gearbox (42) in use. The accessory gearbox (42) may be axially mounted and may provide a bridge for supporting a plurality of conduits.

    GAS TURBINE ENGINE INNER BARREL
    4.
    发明申请
    GAS TURBINE ENGINE INNER BARREL 审中-公开

    公开(公告)号：US20190323383A1

    公开(公告)日：2019-10-24

    申请号：US16378931

    申请日：2019-04-09

    申请人： ROLLS-ROYCE plc

    发明人： Lucian INGLEY ,  Clare L. BEWICK

    IPC分类号： F01D25/26 ,  F02C3/06

    摘要： A gas turbine engine for an aircraft is provided. The gas turbine engine comprises an engine core comprising a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor. The gas turbine engine further comprises a fan located upstream of the engine core, the fan comprising a plurality of fan blades, the fan generating a core airflow which enters the engine core and a bypass airflow which flows through a bypass duct surrounding the engine core. The gas turbine engine further comprises a circumferential row of outer guide vanes located in the bypass duct rearwards of the fan, the outer guide vanes extending radially outwardly from an inner ring which defines a radially inner surface of the bypass duct.