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

    公开(公告)号：US20200025035A1

    公开(公告)日：2020-01-23

    申请号：US16378847

    申请日：2019-04-09

    Applicant: ROLLS-ROYCE plc

    Inventor： Richard PEACE ,  Lucian INGLEY

    IPC: F01D25/24 ,  F02K1/09 ,  F02K3/06

    Abstract: 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.

    GAS TURBINE ENGINE FIREPROOFING
    3.
    发明申请
    GAS TURBINE ENGINE FIREPROOFING 审中-公开

    公开(公告)号：US20190107056A1

    公开(公告)日：2019-04-11

    申请号：US16142109

    申请日：2018-09-26

    Applicant: ROLLS-ROYCE plc

    Inventor： Richard PEACE

    IPC: F02C7/25 ,  F02C7/32

    Abstract: A gas turbine engine has a nacelle providing an external skin of the engine, a casing structure radially inwards of the external skin and providing an outer surface of an air flow duct of the engine, and plural engine components located in the bay formed between the casing structure and the nacelle. The components are part of either a first set of components or a second set of components. The components of the first set are all the components from the bay which are potential ignition sources, and the components of the second set are all the remaining components from the bay. The engine further has a container located in the bay, the container being fireproof capable of withstanding the application of heat by a standard flame for 15 minutes and the container containing the components of the first set.

    METHOD OF SERVICING A GAS TURBINE ENGINE
    4.
    发明申请
    METHOD OF SERVICING A GAS TURBINE ENGINE 有权
    维修燃气涡轮发动机的方法

    公开(公告)号：US20130160291A1

    公开(公告)日：2013-06-27

    申请号：US13716648

    申请日：2012-12-17

    Applicant: ROLLS-ROYCE PLC

    Inventor： Paul BROUGHTON ,  Richard PEACE

    IPC: B23P6/00

    CPC classification number: B23P6/005 ,  F02C7/32 ,  F05D2230/60 ,  F05D2230/70 ,  F05D2230/72 ,  Y02T50/672 ,  Y10T29/49238

    Abstract: A gas turbine engine 10 is provided with rigid raft assemblies 290, which may be electrical harness raft assemblies 290 comprising electrical conductors embedded in a rigid composite material. The rigid raft assemblies 290 can be provided with engine dressings, such as pipework and ECUs to produce an electrical raft assembly. In order to assemble or dress the gas turbine engine 10, the rigid raft assemblies can be pre-prepared to incorporate at least a part of at least one gas turbine engine system/component before being installed on the gas turbine engine 10. During maintenance, whole raft assemblies can be removed and replaced with corresponding, pre-prepared assemblies. This can save considerable time during engine build and maintenance.

    Abstract translation: 燃气涡轮发动机10设置有刚性筏组件290，其可以是包括嵌入刚性复合材料中的电导体的电气筏组件290。 刚性筏组件290可以设置有发动机敷料，例如管道和ECU，以产生电筏组件。 为了组装或装饰燃气涡轮发动机10，可以预先准备刚性筏组件以在安装在燃气涡轮发动机10上之前并入至少一个燃气涡轮发动机系统/部件的至少一部分。在维护期间， 整个筏组件可以拆下并用相应的预先准备的组件替换。 这可以在发动机制造和维护期间节省大量时间。

    BRACKET FOR A GAS TURBINE ENGINE
    5.
    发明申请
    BRACKET FOR A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20200300126A1

    公开(公告)日：2020-09-24

    申请号：US16815513

    申请日：2020-03-11

    Applicant: ROLLS-ROYCE plc

    Inventor： Richard PEACE ,  Daniel CUTTING ,  Yuri FREY ,  John P WOOTTON

    IPC: F01D25/28 ,  F02C7/00

    Abstract: The present disclosure relates to a bracket for a gas turbine engine, the bracket comprising an engine fixing for attaching the bracket to the gas turbine engine at a first end of the bracket, a payload fixing for attaching a payload to the bracket at a second end of the bracket; and a box section comprising a first wall having a first curved shape and extending from the first end to the second end, a second wall having a second curved shape and extending from the first end to the second end, and a plurality of separation members arranged to rigidly fix the first wall relative to the second wall.

    SUPPORTED TERMINATION
    6.
    发明申请
    SUPPORTED TERMINATION 有权
    支持终止

    公开(公告)号：US20160156112A1

    公开(公告)日：2016-06-02

    申请号：US14953148

    申请日：2015-11-27

    Applicant: ROLLS-ROYCE plc

    Inventor： Paul BROUGHTON ,  Richard PEACE

    IPC: H01R4/70

    CPC classification number: H01R4/70 ,  H01R4/30 ,  H01R4/34 ,  H01R9/22 ,  H01R11/12 ,  H01R13/447 ,  H01R13/5213 ,  H01R13/533

    Abstract: The present invention relates to an assembly for the improved connection or termination of one or more minerally insulated cables, the assembly comprising an electrically insulating plate comprising one or more channels to accommodate and support one or more inward cables; one or more channels to accommodate and support one or more outward cables; one or more recesses to accommodate one or more electrical components; one or more terminal studs arranged to connect said at least one inward and outward cable; and a protective cover comprising one or more protective plates locatable over the electrically insulating plate and cables and further comprising one or more recesses located so as to provide access to each of the one or more terminal studs.

    Abstract translation: 本发明涉及一种用于改进一个或多个矿物绝缘电缆的连接或终止的组件，该组件包括电绝缘板，该电绝缘板包括用于容纳和支撑一个或多个向内电缆的一个或多个通道; 一个或多个通道以容纳和支撑一个或多个向外的电缆; 一个或多个凹部以容纳一个或多个电气部件; 一个或多个端子柱，被布置成连接所述至少一个向内和向外的电缆; 以及保护盖，其包括位于所述电绝缘板和电缆上的一个或多个保护板，并且还包括一个或多个凹部，所述凹部位于所述一个或多个端子柱中的每一个上。

    GAS TURBINE ENGINE
    7.
    发明申请
    GAS TURBINE ENGINE 有权
    气体涡轮发动机

    公开(公告)号：US20150101331A1

    公开(公告)日：2015-04-16

    申请号：US14487835

    申请日：2014-09-16

    Applicant: ROLLS-ROYCE PLC

    Inventor： Robert GOULDS ,  Brian Richard LACE ,  Richard PEACE

    IPC: F02C7/32 ,  F02C7/28 ,  F02C7/18 ,  F02C3/14

    CPC classification number: F02C7/32 ,  F01D25/08 ,  F01D25/12 ,  F01D25/14 ,  F01D25/145 ,  F02C3/14 ,  F02C6/04 ,  F02C6/06 ,  F02C6/08 ,  F02C7/12 ,  F02C7/125 ,  F02C7/18 ,  F02C7/24 ,  F02C7/25 ,  F02C7/28 ,  F05D2260/20 ,  F05D2260/50 ,  F16C1/10 ,  F16C1/103 ,  F16C1/262 ,  F16C2360/23

    Abstract: A gas turbine engine having a fire wall that is configured to provide a fire resistant barrier between a first zone and a second zone in the gas turbine engine, the second zone being hotter than the first zone when the gas turbine engine is in use. The gas turbine also has an actuator that is located in the first zone and is configured to generate a mechanical force when operated, an actuatable device that is located in the second zone and is configured to be actuated by a mechanical force and a mechanical force transmitting device that extends from the actuator to the actuatable device via a hole in the fire wall. The mechanical force transmitting device is configured to, when the actuator is operated, actuate the actuatable device by transmitting a mechanical force generated by the actuator to the actuatable device.

    Abstract translation: 一种具有防火墙的燃气涡轮发动机，其被配置为在所述燃气涡轮发动机中的第一区域和第二区域之间提供耐火屏障，当所述燃气涡轮发动机正在使用时，所述第二区域比所述第一区域热。 燃气轮机还具有致动器，该致动器位于第一区域中并被构造成在被操作时产生机械力，位于第二区域中的致动装置，并被构造成由机械力和机械力传递 装置，其通过防火墙中的孔从致动器延伸到可致动装置。 机械力传递装置构造成当致动器被操作时，通过将由致动器产生的机械力传递到可致动装置来致动可致动装置。

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