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    DUCT ARRANGEMENT
    11.
    发明申请
    DUCT ARRANGEMENT 有权
    道路安排

    公开(公告)号：US20140150919A1

    公开(公告)日：2014-06-05

    申请号：US14087623

    申请日：2013-11-22

    Applicant: ROLLS-ROYCE PLC

    Inventor： John Richard WEBSTER ,  Paul John NEWTON ,  Paul FLETCHER

    IPC: F16L9/00

    CPC classification number: F16L9/00 ,  B63H11/00 ,  B63H11/04 ,  B63H11/103 ,  B63H2011/004 ,  B63H2011/043

    Abstract: A duct arrangement 18 for a waterjet propulsor 10. The duct arrangement 18 comprises a main duct 30 having an inlet 20. The inlet 20 has an elongate main portion 32 extending along a principal axis 34, and at least one lateral portion 36 in fluid communication with the main portion 34. The at least one lateral portion 36 extends part way only along the length of the main portion 34.

    Abstract translation: 用于水射流推进器10的管道装置18.管道装置18包括具有入口20的主管道30.入口20具有沿主轴线34延伸的细长主体部分32和与流体连通的至少一个横向部分36 主体部分34.至少一个横向部分36仅沿主体部分34的长度部分地延伸。

    METHOD OF CONTRAIL MITIGATION AND AIRCRAFT HAVING CONTRAIL MITIGATION FUNCTIONALITY
    12.
    发明公开
    METHOD OF CONTRAIL MITIGATION AND AIRCRAFT HAVING CONTRAIL MITIGATION FUNCTIONALITY 审中-公开

    公开(公告)号：US20240068414A1

    公开(公告)日：2024-02-29

    申请号：US18503750

    申请日：2023-11-07

    Applicant: ROLLS-ROYCE plc

    Inventor： Paul FLETCHER ,  Peter SWANN

    IPC: F02C9/28 ,  F02C9/42 ,  F02C9/44

    CPC classification number: F02C9/28 ,  F02C9/42 ,  F02C9/44 ,  F05D2220/323 ,  F05D2270/051 ,  F05D2270/311 ,  F05D2270/313

    Abstract: A method of mitigating contrails produced by an aircraft having a set of gas turbine engines, comprises the steps of (i) for each engine in a first subset of the engines, reducing the operating efficiency of the engine to produce a reduction in thrust provided by that engine and (ii) for each engine in a second subset, increasing the fuel flow to the engine to increase the thrust provided by that engine, the set of at least two gas turbine engines consisting of the first and second subsets. The method provides for contrail mitigation action by means of engine operating efficiency reduction to be directed to a first subset of engines for which contrail mitigation per unit engine operating efficiency reduction is greatest, the resulting reduction in thrust provided by such engines being at least partially compensated by increasing fuel flow to engines of the second subset.

    BEARING ARRANGEMENT AND METHOD
    14.
    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。

    BEARING STRUCTURE
    15.
    发明申请
    BEARING STRUCTURE 有权
    轴承结构

    公开(公告)号：US20160160911A1

    公开(公告)日：2016-06-09

    申请号：US14961124

    申请日：2015-12-07

    Applicant: ROLLS-ROYCE PLC

    Inventor： Stephen GALLIMORE ,  Paul FLETCHER ,  Philip PETERS

    IPC: F16C19/54 ,  F01D25/16 ,  F16C19/52 ,  F16C19/06 ,  F16C33/78 ,  F16C35/04

    CPC classification number: F16C19/54 ,  F01D25/16 ,  F01D25/164 ,  F02C7/06 ,  F05D2220/32 ,  F05D2240/54 ,  F05D2260/15 ,  F16C19/06 ,  F16C19/16 ,  F16C19/522 ,  F16C19/542 ,  F16C25/08 ,  F16C33/7823 ,  F16C35/042 ,  F16C41/02 ,  F16C2360/23

    Abstract: Load sharing stacked bearing structure including first bearing having a first inner race, first outer race and first set of roller elements housed between first inner race and first outer race and a second bearing having a second inner race, second outer race and second set of roller elements housed between second inner race and the second outer race. A housing surrounds the first and second bearings. First compliant element is provided with the first compliant element connected between the housing and the first outer race. The first compliant element, first outer race and housing define at a pressure chamber. The first outer race axially slidable relative to the second outer race such that an increase in pressure in pressure chamber causes a change in axial spacing between the outer races. This induces an additional axial load on the bearings which helps balance thrust load sharing.

    Abstract translation: 负载共享层叠轴承结构包括具有第一内圈，第一外圈和容纳在第一内圈和第一外圈之间的第一组滚子元件的第一轴承和具有第二内圈，第二外圈和第二组滚子的第二轴承 容纳在第二内圈和第二外圈之间的元件。 壳体围绕第一和第二轴承。 第一顺应元件设置有连接在壳体和第一外座圈之间的第一顺应元件。 第一顺应元件，第一外圈和外壳限定在压力室。 第一外座圈相对于第二外座圈可轴向滑动，使得压力室中的压力增加导致外座圈之间的轴向间距的变化。 这会在轴承上产生额外的轴向载荷，有助于平衡推力负荷分担。

    METHOD OF CONTRAIL MITIGATION AND AIRCRAFT HAVING CONTRAIL MITIGATION FUNCTIONALITY
    16.
    发明申请
    METHOD OF CONTRAIL MITIGATION AND AIRCRAFT HAVING CONTRAIL MITIGATION FUNCTIONALITY 有权

    公开(公告)号：US20220403790A1

    公开(公告)日：2022-12-22

    申请号：US17829896

    申请日：2022-06-01

    Applicant: ROLLS-ROYCE plc

    Inventor： Paul FLETCHER ,  Peter SWANN

    IPC: F02C9/28 ,  F02C9/42 ,  F02C9/44

    Abstract: A method of mitigating contrails produced by an aircraft having a set of gas turbine engines, comprises the steps of (i) for each engine in a first subset of the engines, reducing the operating efficiency of the engine to produce a reduction in thrust provided by that engine and (ii) for each engine in a second subset, increasing the fuel flow to the engine to increase the thrust provided by that engine, the set of at least two gas turbine engines consisting of the first and second subsets. The method provides for contrail mitigation action by means of engine operating efficiency reduction to be directed to a first subset of engines for which contrail mitigation per unit engine operating efficiency reduction is greatest, the resulting reduction in thrust provided by such engines being at least partially compensated by increasing fuel flow to engines of the second subset.

    SUPERCRITICAL FLUID HEAT ENGINE
    17.
    发明申请
    SUPERCRITICAL FLUID HEAT ENGINE 有权

    公开(公告)号：US20170254229A1

    公开(公告)日：2017-09-07

    申请号：US15426577

    申请日：2017-02-07

    Applicant: ROLLS-ROYCE PLC

    Inventor： Paul FLETCHER

    IPC: F01K25/10 ,  F01K7/16 ,  F01K11/02 ,  F01K23/10

    CPC classification number: F01K25/103 ,  F01K7/165 ,  F01K11/02 ,  F01K23/10 ,  F02C1/10 ,  F02C1/105 ,  F02C6/00 ,  F02C6/14 ,  F02C6/16 ,  F02C6/18 ,  F05D2260/611 ,  Y02E20/16

    Abstract: A supercritical working fluid closed cycle heat engine includes, in fluid flow series: a heat source heat exchanger configured to raise the temperature of a working fluid; an expander configured to extract work from the working fluid; a condenser configured to exchange heat between the working fluid and the cooling medium; and a separator configured to separate liquid phase working fluid from gaseous phase working fluid and deliver gaseous phase working fluid to a gaseous compressor and liquid phase working fluid to a fixed displacement liquid pump, the compressor and pump being arranged in parallel. Each of the compressor and fixed displacement pump are configured to return fluid to the heat source heat exchanger. The compressor comprises a variable inlet guide vane and a variable outlet diffuser vane.

    BEARING STRUCTURE
    18.
    发明申请
    BEARING STRUCTURE 有权
    轴承结构

    公开(公告)号：US20160160910A1

    公开(公告)日：2016-06-09

    申请号：US14961027

    申请日：2015-12-07

    Applicant: ROLLS-ROYCE plc

    Inventor： Stephen GALLIMORE ,  Paul FLETCHER

    IPC: F16C19/54 ,  F01D25/16 ,  F16C35/04 ,  F16C33/78 ,  F16C19/52 ,  F16C19/06

    CPC classification number: F16C19/54 ,  F01D25/16 ,  F01D25/164 ,  F02C7/06 ,  F05D2220/32 ,  F05D2240/54 ,  F05D2260/15 ,  F16C19/06 ,  F16C19/16 ,  F16C19/522 ,  F16C25/08 ,  F16C33/7816 ,  F16C35/042 ,  F16C41/02 ,  F16C2360/23

    Abstract: Bearing structure including a first bearing, surrounded by a housing, having a first inner and outer race and first set of rolling elements between the inner and outer races and a second bearing having a second inner and outer race and second set of rolling elements between the second inner and outer races. A first compliant element is connected to the first outer race. A rigid diaphragm is connected to the first outer race between the compliant element and outer race, and is connected to the housing at its outer end. The first compliant element, outer race and rigid diaphragm at least partly define a pressure chamber. The first outer race is axially slidable relative to the second such that a pressure increase in the chamber changes the axial spacing between the first and second outer races, inducing additional axial load on the bearings which helps balance thrust load sharing.

    Abstract translation: 轴承结构包括由壳体包围的第一轴承，具有第一内圈和外座圈以及在第一和第二座圈之间的第一组滚动元件，以及第二轴承，其具有第二内外圈和第二组滚动元件 第二次内外赛。 第一顺应元件连接到第一外圈。 刚性膜片在顺应元件和外座圈之间连接到第一外圈，并且在其外端处连接到壳体。 第一顺应元件，外圈和刚性隔膜至少部分地限定压力室。 第一外圈相对于第二外圈可轴向滑动，使得腔室中的压力增加改变了第一和第二外圈之间的轴向间隔，从而在轴承上引起额外的轴向载荷，这有助于平衡推力负载共享。

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