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21 条记录 (耗时 0.014 秒)

    APPARATUS FOR GAS TURBINE ENGINES
    1.
    发明公开
    APPARATUS FOR GAS TURBINE ENGINES 审中-公开

    公开(公告)号：EP3594477A1

    公开(公告)日：2020-01-15

    申请号：EP19179242.3

    申请日：2019-06-10

    申请人： Rolls-Royce plc

    发明人： Maguire, Alan ,  Stretton, Richard

    IPC分类号： F02C7/32 ,  F02C7/36

    摘要： Apparatus for a gas turbine engine, the apparatus comprising: a core engine casing having a longitudinal axis and including: an inner wall defining at least part of a core airflow path through the gas turbine engine; an outer wall defining an external surface of the core engine casing, a first cavity being defined between the inner wall and the outer wall of the core engine casing; a plurality of guide vanes extending radially from the outer wall of the core engine casing; a torque box defined within the first cavity of the core engine casing and at least partially overlapping axially with the plurality of guide vanes, the torque box defining a second cavity; and an accessory gear box positioned within the second cavity of the torque box.

    Axial flow machine cooling system
    4.
    发明公开
    Axial flow machine cooling system 审中-公开
    KühlsystemfürAxialströmungsmaschine

    公开(公告)号：EP2843191A1

    公开(公告)日：2015-03-04

    申请号：EP14180792.5

    申请日：2014-08-13

    申请人： Rolls-Royce plc

    发明人： Maguire, Alan ,  Scanlon, Timothy ,  Young, Colin

    IPC分类号： F01D5/08 ,  F01D25/12 ,  F02C7/12

    CPC分类号： F02C7/18 ,  F01D5/046 ,  F01D5/08 ,  F01D5/081 ,  F01D5/082 ,  F01D9/06 ,  F01D25/08 ,  F01D25/12 ,  F02C3/00 ,  F02C6/08 ,  F02C7/12 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2260/205 ,  Y02T50/676

    摘要： This invention concerns a system for cooling components in a gas turbine engine, the gas turbine engine comprising a compressor for driving a primary gas flow to a combustor and a turbine arranged to be driven by combustion gases from the combustor, wherein the system comprises: an annular cooling flow passage arranged for fluid communication between the compressor and the turbine, the flow passage having a first inlet arranged to receive gas from the primary gas flow downstream of compressor, and a second inlet located upstream of the first inlet, wherein the annular cooling flow passage has at least one internal wall for guiding airflow from the first inlet towards the airflow from the second inlet, such that the airflow from the first and second inlets coalesce within the annular flow passage prior to passing along the flow passage in a direction from the compressor to the turbine. The internal wall may guide the airflow from the first inlet in a rearward direction from the turbine to the compressor.

    摘要翻译： 本发明涉及一种用于在燃气涡轮发动机中冷却部件的系统，所述燃气涡轮发动机包括用于驱动燃烧器的主气流的压缩机和布置成由来自燃烧器的燃烧气体驱动的涡轮机，其中该系统包括： 环形冷却流道设置成用于压缩机和涡轮机之间的流体连通，该流动通道具有布置成从压缩机下游的主气流接收气体的第一入口和位于第一入口上游的第二入口，其中环形冷却 流动通道具有至少一个内壁，用于引导来自第一入口的气流朝向来自第二入口的气流，使得来自第一入口和第二入口的气流在沿着流动通道沿着从 压缩机到涡轮机。 内壁可以将从第一入口的气流沿涡轮机向后的方向引导到压缩机。

    GAS TURBINE ENGINE
    5.
    发明公开
    GAS TURBINE ENGINE 审中-公开

    公开(公告)号：EP3696376A1

    公开(公告)日：2020-08-19

    申请号：EP19216659.3

    申请日：2019-12-16

    申请人： Rolls-Royce plc

    发明人： Maguire, Alan ,  Thornton, Stewart ,  Bond, Philip ,  Knight, Glenn

    IPC分类号： F01D5/06 ,  F01D25/16 ,  F02C7/06

    摘要： A gas turbine engine (10, 41) for an aircraft. The gas turbine engine comprises a rotatable shaft (45) defining a rotational axis extending between rearward and forward ends of the gas turbine engine and a compressor drum (43) surrounding, and coupled to, the shaft so as to define an annular gap therebetween. An intermediate case (44) is arranged axially rearward of the compressor drum and comprising a bearing support element (46) extending into the annular gap. A rearward bearing (63) is mounted between the intermediate case and the shaft. A forward bearing (47) is forward of the rearward bearing, mounted between the bearing support element (46) and the shaft (45), and proximate a forward end of the compressor drum (43).

    A DRIVESHAFT
    7.
    发明公开
    A DRIVESHAFT 审中-公开

    公开(公告)号：EP3527802A1

    公开(公告)日：2019-08-21

    申请号：EP19151814.1

    申请日：2019-01-15

    申请人： Rolls-Royce plc

    发明人： Maguire, Alan

    IPC分类号： F02C7/36

    摘要： A turbofan engine driveshaft comprises, in axial sequence along an axial centreline, a driving portion, and a driven portion. The driving portion has a first end and a second end. The second end of driving portion is connected to the driven portion. The driven portion comprises an annular drum having a radially inwardly facing surface, with the annular drum having a stiffener attached to the radially inwardly facing surface.
    The driveshaft is supported radially by a bearing assembly at the connection between the driving portion and the driven portion. The driving portion is configured to accommodate a predetermined range of movement of the outer end relative to the inner end.

    CABIN BLOWER SYSTEM
    8.
    发明公开
    CABIN BLOWER SYSTEM 有权
    客舱鼓风机系统

    公开(公告)号：EP3208195A1

    公开(公告)日：2017-08-23

    申请号：EP17153055.3

    申请日：2017-01-25

    申请人： Rolls-Royce plc

    发明人： Knight, Glenn ,  Maguire, Alan ,  Sharpe, Richard

    IPC分类号： B64D13/04

    CPC分类号： B64D13/00 ,  B64D13/04 ,  B64D2013/0696 ,  F01D13/00 ,  F01D17/16 ,  F02C7/26 ,  F02C7/277 ,  F02C7/32 ,  F05D2220/323 ,  F05D2260/406 ,  F05D2260/85 ,  Y02T50/44 ,  Y02T50/671

    摘要： An aircraft cabin blower system is described having a hydraulic circuit comprising a first hydraulic device and a second hydraulic device. The first hydraulic device is mechanically coupled to a cabin blower compressor and the second hydraulic device is arranged in use to be mechanically coupled to a spool of a gas turbine engine. The first hydraulic device is capable of performing as a hydraulic motor and the second hydraulic device is capable of performing as a hydraulic pump. When, in use, the system is operating in a cabin blower configuration, a driving force supplied by the spool of the gas turbine causes the second hydraulic device to pump liquid provided in the hydraulic circuit and thereby to drive the first hydraulic device, which in turn rotates the cabin blower compressor.

    摘要翻译： 描述了具有包括第一液压装置和第二液压装置的液压回路的飞机机舱送风机系统。 第一液压装置机械地联接至座舱鼓风机压缩机，并且第二液压装置在使用中布置为机械联接至燃气涡轮发动机的阀芯。 第一液压装置能够用作液压马达，第二液压装置能够用作液压泵。 在使用中，当系统在机舱送风机构造中操作时，由燃气轮机的阀芯供应的驱动力使得第二液压装置泵送液压回路中提供的液体并且由此驱动第一液压装置，该第一液压装置在 转动机舱鼓风机压缩机。

    SYSTEM FOR SUPPLYING LUBRICANT TO A COMPONENT
    10.
    发明公开
    SYSTEM FOR SUPPLYING LUBRICANT TO A COMPONENT 审中-公开

    公开(公告)号：EP3869015A1

    公开(公告)日：2021-08-25

    申请号：EP21150826.2

    申请日：2021-01-11

    申请人： Rolls-Royce plc

    发明人： Maguire, Alan ,  Sharpe, Richard ,  Davies, Neil

    IPC分类号： F01D25/20 ,  F02C7/36 ,  F01D21/00

    摘要： A system (200, 300, 360, 370, 400, 500) for supplying lubricant to a component (202) of a gas turbine engine (10) having a fan shaft (26) is provided. The system (200, 300, 360, 370, 400, 500) includes a pump (204) drivably couplable to the fan shaft (26) for pumping lubricant to the component (202). The pump (204) includes an inlet (206) for receiving lubricant from a lubricant source (208), an outlet (210) for outputting lubricant to the component (202) and a swashplate (220) movable between at least a first position (P1) and a second position (P2). The system (200, 300, 360, 370, 400, 500) also includes a swashplate actuator (222, 522) for actuating the swashplate (220) between the first position (P1) and the second position (P2) according to whether the fan shaft (26) is rotating in a forward direction (F) or a reverse direction (R) opposite to the forward direction (F).