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    BEARING ARRANGEMENTS
    1.
    发明申请
    BEARING ARRANGEMENTS 审中-公开

    公开(公告)号：US20170219009A1

    公开(公告)日：2017-08-03

    申请号：US15408180

    申请日：2017-01-17

    申请人： ROLLS-ROYCE plc

    发明人： Paul FLETCHER ,  Paul WILSON

    IPC分类号： F16C32/04

    CPC分类号： F16C32/0474 ,  F16C19/52 ,  F16C25/08 ,  F16C25/086 ,  F16C41/008 ,  F16C2233/00 ,  F16C2360/23

    摘要： A bearing arrangement comprising: a first bearing including a first inner race coupled to a rotatable component, a first outer race; and a plurality of first roller elements between the first inner race and the first outer race; a second bearing including a second inner race coupled to the rotatable component, a second outer race, and a plurality of second roller elements between the second inner race and the second outer race; a component, the first outer race being axially moveable relative to the component; and a member between the first bearing and the second bearing and arranged to provide an indirect first force on the first outer race to prevent the first roller elements from skidding when the first bearing and the second bearing receive a second force in a first direction, the second bearing being configured to transfer the second force to the component.

    AIRCRAFT VAPOUR TRAIL CONTROL SYSTEM
    2.
    发明申请
    AIRCRAFT VAPOUR TRAIL CONTROL SYSTEM 审中-公开
    飞机蒸汽拖车控制系统

    公开(公告)号：US20160376918A1

    公开(公告)日：2016-12-29

    申请号：US15163318

    申请日：2016-05-24

    申请人： ROLLS-ROYCE plc

    发明人： Peter SWANN ,  Andrew M. ROLT ,  Paul FLETCHER

    IPC分类号： F01D21/00 ,  B64D27/18 ,  F02K3/06 ,  B64D27/24 ,  F02C3/04 ,  F02C7/22

    CPC分类号： F01D21/003 ,  B64C21/025 ,  B64C23/065 ,  B64D27/18 ,  B64D27/24 ,  B64D2027/026 ,  F01D15/10 ,  F01D17/24 ,  F02C3/04 ,  F02C7/22 ,  F02K3/06 ,  F02K3/075 ,  F05D2220/323 ,  F05D2260/42 ,  F05D2270/306

    摘要： The invention concerns an aircraft propulsion system having an engine core within which fuel is combusted to produce an exhaust containing water produced from the combustion of fuel, at least one propulsive fan for generating a mass flow of air which mixes with the exhaust of the engine core, and one or more sensor arranged to sense a condition indicative of vapour trail formation by the exhaust flow from the engine; and a controller arranged to control the ratio of the mass flow of water in the exhaust to the mass flow of air propulsed by the propulsive fan such that the ratio is reduced upon sensing of said condition by the one or more sensor.

    摘要翻译： 本发明涉及一种具有发动机芯的飞行器推进系统，其中燃料被燃烧以产生包含由燃料燃烧产生的水的排气，至少一个推进风扇，用于产生与发动机芯的排气混合的大量空气流 以及一个或多个传感器，其被布置成感测通过来自发动机的排气流指示蒸气轨道形成的状况; 以及控制器，其布置成控制排气中的水质量流与由推进风扇推进的空气的质量流量的比率，使得在通过一个或多个传感器感测到所述条件时，比率减小。

    GAS TURBINE ENGINE AND METHOD OF OPERATION
    4.
    发明申请
    GAS TURBINE ENGINE AND METHOD OF OPERATION 审中-公开
    气体涡轮发动机及其运行方法

    公开(公告)号：US20160053721A1

    公开(公告)日：2016-02-25

    申请号：US14815115

    申请日：2015-07-31

    申请人： ROLLS-ROYCE PLC

    发明人： Paul FLETCHER ,  Anthony John MORAN ,  Malcolm Laurence HILLEL ,  Philip Patrick WALSH

    IPC分类号： F02K3/02 ,  F02K3/04 ,  F01D17/16 ,  F02K3/115

    CPC分类号： F02C9/18 ,  F02C9/54

    摘要： A gas turbine engine (20) comprising a variable geometry engine compressor (24), a variable geometry engine turbine (30) coupled to the engine compressor (24) and a combustor (28). The combustor (28) has an inlet (34) arranged to receive air from a first engine compressor outlet (34), and an outlet arranged to deliver combustion products to the engine turbine (30); a combustor bypass passage (50) having an inlet (53) arranged to receive air from a second engine compressor outlet (53), and an outlet (54) in fluid communication with a main fluid flow path downstream of a combustion zone (46, 48) of the combustor (28), and upstream of a turbine inlet (31); wherein the combustor bypass passage (50) comprises a bypass control valve (52) configured to selectively modulate the ratio of air flowing to the combustor inlet (34) to air flowing through the bypass passage (50).

    摘要翻译： 一种燃气涡轮发动机（20），包括可变几何发动机压缩机（24），耦合到发动机压缩机（24）的可变几何发动机涡轮机（30）和燃烧器（28）。 燃烧器（28）具有设置成从第一发动机压缩机出口（34）接收空气的入口（34）和布置成将燃烧产物输送到发动机涡轮机（30）的出口; 具有布置成从第二发动机压缩机出口（53）接收空气的入口（53）的燃烧器旁路通道（50）和与燃烧区（46,46）下游的主流体流动路径流体连通的出口（54） （28）的上游和涡轮机入口（31）的上游; 其中所述燃烧器旁路通道（50）包括旁通控制阀（52），所述旁路控制阀（52）构造成选择性地调节流过所述燃烧器入口（34）的空气与流过所述旁路通道（50）的空气的比例。

    AIRCRAFT VAPOUR TRAIL CONTROL SYSTEM
    5.
    发明申请
    AIRCRAFT VAPOUR TRAIL CONTROL SYSTEM 有权
    飞机蒸汽拖车控制系统

    公开(公告)号：US20150285158A1

    公开(公告)日：2015-10-08

    申请号：US14644799

    申请日：2015-03-11

    申请人： ROLLS-ROYCE PLC

    发明人： Malcolm HILLEL ,  Peter SWANN ,  Andrew Martin ROLT ,  Paul FLETCHER

    IPC分类号： F02C9/20 ,  B64D31/06 ,  B64D33/04 ,  F02K1/76

    CPC分类号： F02C9/20 ,  B64D31/06 ,  B64D33/04 ,  F02K1/1207 ,  F02K1/16 ,  F02K1/76 ,  F02K1/825 ,  F02K3/075 ,  F05D2220/323 ,  F05D2270/08 ,  F05D2270/311 ,  F05D2270/312 ,  F05D2270/313 ,  Y02T50/677

    摘要： The invention concerns an aircraft propulsion control system in which a gas turbine engine has an actuable flow opening for control of flow to or from a portion of the engine. One or more sensor is arranged to sense a condition indicative of vapour trail formation by the exhaust flow from the engine. A controller is arranged to control actuation of the flow opening so as to reduce the efficiency of the engine upon sensing of said condition by the one or more sensor. In one example, the flow opening is a variable area fan nozzle.

    摘要翻译： 本发明涉及一种飞机推进控制系统，其中燃气涡轮发动机具有用于控制流向或来自发动机的一部分的流动的可启动流动开口。 一个或多个传感器被布置成通过来自发动机的排气流感测指示蒸气轨道形成的状况。 控制器被布置成控制流动开口的致动，以便在通过一个或多个传感器检测到所述状态时降低发动机的效率。 在一个示例中，流动开口是可变区域风扇喷嘴。

    COMBINED REFRIGERATION AND POWER PLANT
    6.
    发明申请
    COMBINED REFRIGERATION AND POWER PLANT 审中-公开

    公开(公告)号：US20190309997A1

    公开(公告)日：2019-10-10

    申请号：US16311569

    申请日：2017-07-10

    申请人： ROLLS-ROYCE PLC

    发明人： Paul FLETCHER ,  Parag VYAS ,  Robert D COLLINS ,  Chloe J PALMER ,  Stephen G BROWN

    IPC分类号： F25B27/00 ,  F25B9/00 ,  F25B9/06

    摘要： A combined refrigeration and power plant. The power plant comprises an internal combustion engine an air cycle machine refrigerator driven by the internal combustion engine and configured to refrigerate atmospheric air to provide working fluid to combined refrigeration and power generation cycle, a refrigerated air storage unit configured to store working fluid produced by the air cycle machine refrigerator; and first and second heat exchangers. The first heat exchanger arrangement is configured to exchange heat between a device to be cooled and the working fluid, and the second heat exchanger arrangement is configured to exchange heat between the working fluid downstream of the first heat exchanger in the combined refrigeration and power generation cycle and waste heat from the internal combustion engine; and a generator turbine configured to receive heated working fluid from the second heat exchanger arrangement, and configured to power an electrical generator.

    Aircraft Electrically-Assisted Propulsion Control System
    7.
    发明申请
    Aircraft Electrically-Assisted Propulsion Control System 审中-公开

    公开(公告)号：US20180178920A1

    公开(公告)日：2018-06-28

    申请号：US15846994

    申请日：2017-12-19

    申请人： ROLLS-ROYCE plc

    发明人： Peter SWANN ,  Paul FLETCHER ,  Alvise PELLEGRINI ,  Ashog KULATHASAN

    IPC分类号： B64D27/24 ,  B64D31/06 ,  F02C9/48

    摘要： This invention concerns an aircraft propulsion system in which an engine has an engine core comprising a compressor, a combustor and a turbine driven by a flow of combustion products of the combustor. At least one propulsive fan generates a mass flow of air to propel the aircraft. An electrical energy store is provided on board the aircraft. At least one electric motor is arranged to drive the propulsive fan and the engine core compressor. A controller controls the at least one electric motor to mitigate the creation of a contrail caused by the engine combustion products by altering the ratio of the mass flow of air by the propulsive fan to the flow of combustion products of the combustor. The at least one electric motor is controlled so as to selectively drive both the propulsive fan and engine core compressor.

    GAS TURBINE ENGINE
    8.
    发明申请
    GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20180149115A1

    公开(公告)日：2018-05-31

    申请号：US15810263

    申请日：2017-11-13

    申请人： ROLLS-ROYCE plc

    发明人： Ahmed M Y RAZAK ,  Paul FLETCHER

    IPC分类号： F02K3/11 ,  F02C3/113 ,  F02K3/10 ,  F02K1/06 ,  F02K3/077 ,  F02K1/38

    摘要： A gas turbine engine may include a high pressure compressor coupled to a high pressure turbine by a high pressure shaft, a core combustor located downstream of the high pressure compressor and upstream of the high pressure turbine, and a low pressure compressor provided upstream of the high pressure compressor. The low pressure compressor may be configured to direct core airflow to the high pressure compressor and first bypass airflow which bypasses the high pressure compressor, core combustor and high pressure turbine through a first bypass duct. The engine may further include a mixer downstream of the high pressure turbine and low pressure compressor, the mixer being configured to mix the core and first bypass airflows. The engine also may include a re-heat combustor configured to combust fuel with both core airflow and first bypass airflow. A low pressure turbine may be provided downstream of the re-heat combustor and coupled to the low pressure compressor (14) by a low pressure shaft, the low pressure and high pressure shafts being independently rotatable. A shaft power transfer arrangement may be provided, which is configured to selectively transfer power between the low pressure and high pressure shafts.

    BEARING APPARATUS AND PIVOT APPARATUS FOR BEARING APPARATUS
    9.
    发明申请
    BEARING APPARATUS AND PIVOT APPARATUS FOR BEARING APPARATUS 审中-公开
    轴承装置的轴承装置和转向装置

    公开(公告)号：US20160123384A1

    公开(公告)日：2016-05-05

    申请号：US14923944

    申请日：2015-10-27

    申请人： ROLLS-ROYCE PLC

    发明人： John R WEBSTER ,  Paul FLETCHER

    IPC分类号： F16C19/52 ,  F16C19/54

    CPC分类号： F16C19/522 ,  F01D25/16 ,  F01D25/162 ,  F16C19/54 ,  F16C41/02 ,  F16C2360/23

    摘要： Bearing apparatus including: a first bearing; a second bearing; and a pivot member including a first part contacting the first bearing, a second part contacting the second bearing, and a fulcrum between the first part and the second part. The pivot member is arranged to pivot about the fulcrum to distribute load between the first bearing and the second bearing.

    摘要翻译： 轴承装置包括：第一轴承; 第二轴承 以及枢转构件，包括接触所述第一轴承的第一部分，接触所述第二轴承的第二部分和所述第一部分与所述第二部分之间的支点。 枢转构件布置成围绕支点枢转以在第一轴承和第二轴承之间分配负载。