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公开(公告)号：US20140090395A1
公开(公告)日：2014-04-03
申请号：US14033878
申请日：2013-09-23
Applicant: ROLLS-ROYCE PLC
Inventor： Ajith APPUKUTTAN , Andrew Martin ROLT , Anthony John MORAN
IPC: F02C7/141
CPC classification number: F02C7/141 , F02C7/185 , F02C7/224 , F05D2260/213 , F05D2270/303 , Y02T50/671 , Y02T50/675 , Y02T50/676
Abstract: A cooling system for a gas turbine engine (10). The system is comprises a fuel air heat exchanger (78) comprising a fuel passage (80) in thermal contact with an engine cooling air passage (82). The system further comprises a fuel deoxygenator (72) located upstream of the fuel air heat exchanger (78) configured to deliver deoxygenated fuel to the fuel air heat exchanger fuel passage (80). The system includes a valve (84) configured to moderate engine cooling air flow to the engine cooling air passage (82).
Abstract translation: 一种用于燃气涡轮发动机（10）的冷却系统。 该系统包括燃料空气热交换器（78），其包括与发动机冷却空气通道（82）热接触的燃料通道（80）。 该系统还包括位于燃料空气热交换器（78）上游的燃料脱氧器（72），其构造成将脱氧燃料输送到燃料空气热交换器燃料通道（80）。 该系统包括构造成调节发动机冷却空气流到发动机冷却空气通道（82）的阀（84）。
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公开(公告)号：US20160123226A1
公开(公告)日：2016-05-05
申请号：US14879833
申请日：2015-10-09
Applicant: ROLLS-ROYCE PLC
Inventor： Ahmed RAZAK , Andrew Martin ROLT
CPC classification number: F02C3/22 , F02C7/18 , F02C7/224 , F05D2240/36 , Y02T50/675
Abstract: There is disclosed a method of operating a gas turbine engine of a type having a compressor section, a combustor section, and a turbine section arranged in flow series. The method involves the steps of: providing a supply of cryogenic liquid fuel; vaporising the cryogenic liquid fuel to produce a gaseous fuel; expanding said gaseous fuel in at least one fuel turbine external to the engine's turbine section; and thereafter directing said expanded gaseous fuel into the engine's combustion section for combustion therein. A related gas turbine arrangement configured for implementation of the method is also disclosed.
Abstract translation: 公开了一种操作具有压缩机段，燃烧器部分和以流动系列布置的涡轮部分的类型的燃气涡轮发动机的方法。 该方法包括以下步骤：提供低温液体燃料; 蒸发低温液体燃料以产生气体燃料; 在发动机涡轮机部分外部的至少一个燃料涡轮机中膨胀所述气体燃料; 然后将所述膨胀的气体燃料引导到发动机的燃烧部分中以在其中燃烧。 还公开了配置用于实施该方法的相关燃气轮机装置。
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公开(公告)号：US20130094963A1
公开(公告)日：2013-04-18
申请号：US13644900
申请日：2012-10-04
Applicant: ROLLS-ROYCE PLC
Inventor： Andrew Martin ROLT
Abstract: This invention relates to a method and apparatus for controlling power distribution in an electrical aircraft propulsive system having at least one electrical propulsion unit which includes a plurality of rotatable blades, each blade having an adjustable pitch; a pitch adjusting mechanism for adjusting the pitch of the blades; at least one electrical machine electrically connected to the electrical propulsion unit so as to provide electrical power when in use; and, a control system, the method comprising the steps of: determining the required propulsion; determining whether the propulsive units are delivering the required propulsion; and, adjusting the pitch angle of the blades of at least one propulsive unit so as to increase or decrease the propulsion provided by that propulsive unit.
Abstract translation: 本发明涉及一种用于控制电气飞机推进系统中的配电的方法和装置，该系统具有至少一个电推进单元，其包括多个可旋转的叶片，每个叶片具有可调节的间距; 用于调节叶片间距的桨距调节机构; 至少一个电机电连接到电推进单元，以便在使用时提供电力; 以及控制系统，所述方法包括以下步骤：确定所需的推进; 确定推进单元是否正在运送所需的推进; 并且调节至少一个推进单元的叶片的桨距角，以便增加或减少由该推进单元提供的推进。
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公开(公告)号：US20130134265A1
公开(公告)日：2013-05-30
申请号：US13672154
申请日：2012-11-08
Applicant: Rolls-Royce PLC
Inventor： Andrew Martin ROLT , Christopher Andrew THOMPSON
CPC classification number: B64D27/18 , B64C9/16 , B64C11/001 , B64C15/00 , B64C2003/147 , B64C2230/20 , B64D27/08 , B64D27/10 , B64D33/02 , B64D33/04 , Y02T50/12 , Y02T50/166 , Y02T50/32
Abstract: An aircraft (10) comprises a wing (12) having a trailing edge (34), a suction surface (14) and a pressure surface (16). The aircraft (10) further comprises a propulsor device (22) having a first inlet (24) and an outlet (30) defined by a passageway. The first inlet (24) is located so as to ingest boundary layer air (56) adjacent the suction surface (14), and the outlet (30). The outlet (30) is located downstream of the trailing edge (34) of the wing (12).
Abstract translation: 飞机（10）包括具有后缘（34），吸力表面（14）和压力表面（16）的翼（12）。 飞行器（10）还包括具有由通道限定的第一入口（24）和出口（30）的推进装置（22）。 第一入口（24）定位成摄取邻近抽吸表面（14）的边界层空气（56）和出口（30）。 出口（30）位于机翼（12）的后缘（34）的下游。
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公开(公告)号：US20130101392A1
公开(公告)日：2013-04-25
申请号：US13644509
申请日：2012-10-04
Applicant: ROLLS-ROYCE PLC
Inventor： Betka REBHI , Lorenzo RAFFAELLI , Andrew Martin ROLT
IPC: F01D13/02
CPC classification number: B64D27/02 , B64C2230/28 , Y02T50/166
Abstract: This invention relates to an aircraft comprising: a first propulsive unit having a first fan with an axis of rotation; and a second propulsive unit local to the first propulsive unit, the second propulsive unit having a second fan with an axis of rotation, wherein the rotational axis of the first fan is proximate to the surface of the aircraft relative to the rotational axis of the second fan such that the first fan ingests boundary layer air when in use.
Abstract translation: 本发明涉及一种飞行器，包括：第一推进单元，具有带旋转轴线的第一风扇; 以及与所述第一推进单元局部的第二推进单元，所述第二推进单元具有带有旋转轴线的第二风扇，其中所述第一风扇的旋转轴线相对于所述第二风扇的旋转轴线接近所述飞行器的表面 风扇使得第一风扇在使用时摄入边界层空气。
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Patent Agency Ranking
公开(公告)号：US20160010590A1
公开(公告)日：2016-01-14
申请号：US14789643
申请日：2015-07-01
Applicant: ROLLS-ROYCE PLC
Inventor： Andrew Martin ROLT
CPC classification number: F02K3/025 , F01D17/143 , F02C3/04 , F02K1/08 , F02K1/09 , F02K1/15 , F02K1/48 , F02K3/06 , F02K3/075 , F05D2220/323 , F05D2250/311 , F05D2250/41 , F05D2260/20 , F05D2260/213 , F05D2260/57 , F05D2260/96 , F05D2270/101 , Y02T50/675
Abstract: A gas turbine engine comprising: a bypass duct having a bypass nozzle; an engine core having a core nozzle; and, a mixer duct defined by a mixer fairing and having a mixer nozzle, wherein the mixer duct is arranged to receive an airflow from the bypass duct through a mixer duct inlet and an airflow from the engine core, when in use, and the geometry of the mixer duct is selectively adjustable by moving the mixer fairing relative to the bypass duct and engine core in use.
Abstract translation: 一种燃气涡轮发动机，包括：具有旁通喷嘴的旁路管道; 具有芯喷嘴的发动机芯; 以及由混合器整流罩限定并具有混合器喷嘴的混合器管道，其中所述混合器管道布置成在使用时从所述旁路管道经由混合器管道入口和来自所述发动机芯的气流接收气流，并且所述几何形状 通过在使用中相对于旁路管道和发动机核心移动混合器整流罩来选择性地调节混合器管道。
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公开(公告)号：US20130336781A1
公开(公告)日：2013-12-19
申请号：US13672333
申请日：2012-11-08
Applicant: ROLLS-ROYCE PLC
Inventor： Andrew Martin ROLT , Christopher Andrew THOMPSON
IPC: B64C21/00
CPC classification number: B64C21/00 , B64C9/16 , B64C11/001 , B64C15/00 , B64C21/06 , B64C2003/147 , B64C2230/20 , B64D27/08 , Y02T50/12 , Y02T50/166 , Y02T50/32
Abstract: An aircraft includes a propulsive fan arrangement having an intake and an exhaust. The fan arrangement is mounted adjacent a gas washed surface of the aircraft in the form of a suction surface of a wing. The intake is separated from the suction surface to define a channel therebetween. The aircraft further includes a Venturi device positioned downstream of the fan exhaust to draw boundary layer air through the channel.
Abstract translation: 飞机包括具有进气和排气的推进式风扇装置。 风扇装置以飞机的吸气表面的形式邻近飞机的气体清洗表面安装。 进气口与抽吸表面分离以在其间限定通道。 飞机还包括位于风扇排气下游的文丘里装置，以通过通道吸引边界层空气。
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公开(公告)号：US20130153184A1
公开(公告)日：2013-06-20
申请号：US13677773
申请日：2012-11-15
Applicant: Rolls-Royce PLC
Inventor： Andrew Martin ROLT , Rory Douglas STIEGER
IPC: F28F3/00
CPC classification number: F28F3/005 , F28D9/0037 , F28F3/046 , F28F2250/106
Abstract: This invention relates to a heat exchanger, comprising a plurality of stacked corrugated plates, each plate having a plurality of parallel main corrugations each having longitudinal peak ridges and trough ridges, wherein either or both of the peak ridges and trough ridges have an undulating profile so as to define a plurality of summits in a common plane.
Abstract translation: 本发明涉及一种热交换器，其包括多个堆叠的波纹板，每个板具有多个平行的主波纹，每个波纹具有纵向峰脊和槽脊，其中峰脊和谷脊中的任一个或两个具有起伏的轮廓，因此 以便在公共平面中定义多个顶点。
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公开(公告)号：US20160010589A1
公开(公告)日：2016-01-14
申请号：US14789483
申请日：2015-07-01
Applicant: ROLLS-ROYCE PLC
Inventor： Andrew Martin ROLT
CPC classification number: F02K3/025 , B64D27/18 , B64D2027/026 , F01D13/003 , F01D15/10 , F02C7/10 , F02C7/143 , F02K1/06 , F02K1/64 , F02K3/04 , F02K3/065 , F05D2220/323 , F05D2220/76 , F05D2270/101 , F05D2270/13 , Y02T50/44 , Y02T50/64 , Y02T50/675
Abstract: A gas turbine engine propulsion system in which a first propulsive unit has a core engine and a first low pressure turbine arranged to be driven by combustion products from the core engine. The first propulsive unit also has a first fan rotor and a first fan shaft drivingly connecting the first turbine and the first fan rotor. The propulsion system also has a further turbine arranged in flow series with the first turbine and a second propulsive unit spaced from the first propulsive unit. The second propulsive unit has a second fan rotor driven by the rotational output of the further turbine. The further turbine may be located in the second propulsive unit and may be in fluid communication with the first turbine via an inter-turbine duct.
Abstract translation: 一种燃气涡轮发动机推进系统，其中第一推进单元具有核心发动机和布置成由来自核心发动机的燃烧产物驱动的第一低压涡轮机。 第一推进单元还具有第一风扇转子和驱动地连接第一涡轮机和第一风扇转子的第一风扇轴。 推进系统还具有与第一涡轮机流动串联布置的另外的涡轮机和与第一推进单元间隔开的第二推进单元。 第二推进单元具有由另外的涡轮机的旋转输出驱动的第二风扇转子。 另外的涡轮机可以位于第二推进单元中，并且可以经由涡轮机间管道与第一涡轮流体连通。
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公开(公告)号：US20150285158A1
公开(公告)日：2015-10-08
申请号：US14644799
申请日：2015-03-11
Applicant: ROLLS-ROYCE PLC
Inventor： Malcolm HILLEL , Peter SWANN , Andrew Martin ROLT , Paul FLETCHER
CPC classification number: 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
Abstract: 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.
Abstract translation: 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。
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