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    BEARING ARRANGEMENT
    1.
    发明申请
    BEARING ARRANGEMENT 有权
    轴承安排

    公开(公告)号：US20140369830A1

    公开(公告)日：2014-12-18

    申请号：US14290512

    申请日：2014-05-29

    Applicant: ROLLS-ROYCE PLC

    Inventor： Paul FLETCHER ,  John Richard WEBSTER ,  Alan Robert MAGUIRE

    IPC: F01D25/16 ,  F16C41/00 ,  F16C37/00

    CPC classification number: F01D25/16 ,  F01D25/162 ,  F02C7/28 ,  F05D2300/174 ,  F05D2300/501 ,  F16C19/10 ,  F16C19/54 ,  F16C25/083 ,  F16C27/08 ,  F16C35/077 ,  F16C37/007 ,  F16C41/004 ,  F16C41/02 ,  F16C2202/08 ,  F16C2204/42 ,  F16C2360/23

    Abstract: A bearing arrangement is disclosed. The bearing arrangement includes first and second bearings, with each bearing including a respective support element and a respective set of rolling elements and defining a respective load path extending through the respective support element and rolling elements. The support elements are coupled such that a load applied to either support element is transmitted through both the first and second load paths. The arrangement further includes a pair of superelastic titanium alloy elements located in the respective load paths to provide resilient movement between the bearings when a load is applied to the bearing arrangement.

    Abstract translation: 公开了一种轴承装置。 轴承装置包括第一和第二轴承，每个轴承包括相应的支撑元件和相应的一组滚动元件，并且限定延伸通过相应支撑元件和滚动元件的相应负载路径。 支撑元件被耦合，使得施加到任一支撑元件的负载通过第一和第二负载路径传输。 该装置还包括位于相应负载路径中的一对超弹性钛合金元件，以在负载施加到轴承装置时在轴承之间提供弹性运动。

    SEAL ARRANGEMENT
    2.
    发明申请
    SEAL ARRANGEMENT 审中-公开
    密封安排

    公开(公告)号：US20160258310A1

    公开(公告)日：2016-09-08

    申请号：US15047194

    申请日：2016-02-18

    Applicant: ROLLS-ROYCE PLC

    Inventor： Lynne Helen TURNER ,  Alan Robert MAGUIRE ,  Sean Alan WALTERS ,  Matthew Kieran DUNK

    IPC: F01D11/02 ,  F16J15/447

    CPC classification number: F01D11/02 ,  F01D11/001 ,  F05D2240/55 ,  F16J15/444

    Abstract: A turbine secondary air system seal arrangement (62). The arrangement comprises a first seal land (70) facing radially inwardly; a second seal land (80) facing radially outwardly; and first labyrinth seal teeth (76) directed radially outwardly to seal against the first seal land (70). Also second labyrinth seal teeth (78) directed radially inwardly to seal against the second seal land (80). The first seal land (70) is configured to move radially relative to the second seal land (80) or the first seal teeth (76) are configured to move radially relatively to the second seal teeth (78) to accommodate differential movement of the lands (70, 80) and teeth (76, 78) during use of the seal arrangement (62).

    Abstract translation: 涡轮机二次空气系统密封装置（62）。 该装置包括面向径向向内的第一密封区域（70） 第二密封面（80）径向向外; 和第一迷宫式密封齿（76）径向向外指向以密封第一密封区（70）。 还有第二迷宫式密封齿（78）径向向内指向以密封第二密封陆地（80）。 第一密封平台（70）构造成相对于第二密封平台（80）径向移动，或者第一密封齿（76）构造成径向地相对于第二密封齿（78）移动，以适应凸台 （70,80）和齿（76,78）在密封装置（62）的使用期间。

    BEARING ARRANGEMENT AND METHOD
    4.
    发明申请
    BEARING ARRANGEMENT AND METHOD 审中-公开
    轴承安装和方法

    公开(公告)号：US20170003196A1

    公开(公告)日：2017-01-05

    申请号：US15264187

    申请日：2016-09-13

    Applicant: ROLLS-ROYCE plc

    Inventor： Stephen GALLIMORE ,  Paul FLETCHER ,  John Richard WEBSTER ,  Alan Robert MAGUIRE

    IPC: G01M13/04 ,  F16C41/02 ,  F16C27/08 ,  F16C19/54 ,  F16C19/52

    CPC classification number: G01M13/04 ,  F01D25/162 ,  F05D2240/52 ,  F05D2260/83 ,  F05D2300/501 ,  F16C19/16 ,  F16C19/522 ,  F16C19/54 ,  F16C19/542 ,  F16C25/083 ,  F16C27/08 ,  F16C33/586 ,  F16C41/02 ,  F16C2233/00 ,  F16C2237/00 ,  F16C2360/23 ,  Y02T50/671

    Abstract: A method of determining the axial load on load-sharing thrust bearings including: providing first and second thrust bearings, each including an inner race and an outer race supported by at least one resilient element; applying a test axial load to each of the first and second thrust bearings to elastically deform the at least one resilient element so as to axially displace the outer race; determining the test axial displacement of each outer race to obtain calibration data comprising values of axial load versus axial displacement; applying an in-service axial load to the first and second thrust bearings to elastically deform the resilient elements so as to axially displace the respective outer races; measuring the in-service axial displacement of each outer race; and based on the measured in-service axial displacements, inferring from the calibration data the values of the in-service axial loads on the first and second thrust bearings.

    Abstract translation: 一种确定负载共享止推轴承上的轴向载荷的方法，包括：提供第一和第二推力轴承，每个包括内座圈和由至少一个弹性元件支承的外座圈; 对所述第一推力轴承和所述第二推力轴承中的每一个施加测试轴向载荷，以使所述至少一个弹性元件弹性变形，从而轴向地移动所述外圈; 确定每个外圈的测试轴向位移以获得包括轴向载荷与轴向位移的值的校准数据; 对第一和​​第二止推轴承施加在役轴向载荷以使弹性元件弹性变形，从而轴向移动相应的外圈; 测量每个外圈的在役轴向位移; 并且基于测量的在役轴向位移，从校准数据推断第一和第二止推轴承上的在用轴向载荷的值。

    AXIAL FLOW MACHINE COOLING SYSTEM
    5.
    发明申请
    AXIAL FLOW MACHINE COOLING SYSTEM 有权
    轴流式冷却系统

    公开(公告)号：US20150047359A1

    公开(公告)日：2015-02-19

    申请号：US14458593

    申请日：2014-08-13

    Applicant: ROLLS-ROYCE PLC

    Inventor： Alan Robert MAGUIRE ,  Timothy John SCANLON ,  Colin YOUNG

    IPC: F02C7/18 ,  F02C3/00

    CPC classification number: 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

    Abstract: This invention concerns a system for cooling components in a gas turbine engine, the gas turbine engine including 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 includes: 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, the airflow from the first and second inlets coalesce within the annular flow passage prior to passing along the passage in a direction from the compressor to the turbine.

    Abstract translation: 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，该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，该流动通道具有第一入口，该第一入口布置成接收来自压缩机下游的主气流的气体，以及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，来自第一入口和第二入口的气流在沿着通道从压缩机方向通过之前在环形流动通道内聚结 涡轮机。

    DRUM SEAL
    6.
    发明申请
    DRUM SEAL 有权
    鼓密封

    公开(公告)号：US20140169953A1

    公开(公告)日：2014-06-19

    申请号：US14095462

    申请日：2013-12-03

    Applicant: ROLLS-ROYCE PLC

    Inventor： Alan Robert MAGUIRE

    IPC: F01D5/06

    CPC classification number: F01D5/06 ,  F01D5/066 ,  F05D2260/60 ,  F05D2260/609 ,  Y02T50/671

    Abstract: A gas turbine engine comprising at least one drum pack having two or more annular discs 62a-c. Adjacent discs 62a-c are connected by drive arms 68 the drum pack is provided with a tubular sealing body 84 positioned radially inwards of the drive arms 68 and extending from a first disc 62a to a last disc 62c in the drum pack. The first 62a and last 62c discs have the greatest axial separation of all discs 62a-c in the drum pack. The sealing body 84 engaging the first 62a and last 62c discs and the engagement being arranged to limit or prevent the ingress of liquid into a drum cavity 76 defined between the first 62a and last 62c discs, the drive arms 68 and the sealing body 84.

    Abstract translation: 一种燃气涡轮发动机，包括具有两个或更多个环形盘62a-c的至少一个鼓包。 相邻的盘62a-c通过驱动臂68连接，鼓包装有设置在驱动臂68径向向内并且从第一盘62a延伸到鼓包中的最后盘62c的管状密封体84。 第一个62a和最后的62c盘具有滚筒包装中所有盘62a-c的最大的轴向分离。 密封体84接合第一62a和最后的62c盘，并且接合被布置成限制或防止液体进入限定在第一62a和最后62c盘之间的鼓腔76中，驱动臂68和密封体84。

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