公开(公告)号：US09739207B2

公开(公告)日：2017-08-22

申请号：US14644799

申请日：2015-03-11

Applicant: ROLLS-ROYCE PLC

Inventor： Malcolm Hillel ,  Peter Swann ,  Andrew Martin Rolt ,  Paul Fletcher

IPC: F02C9/20 ,  B64D33/04 ,  B64D31/06 ,  F02K1/76 ,  F02K1/12 ,  F02K1/16 ,  F02K3/075

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 vapor 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.

公开(公告)号：US09759130B2

公开(公告)日：2017-09-12

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 ,  F02C7/18 ,  F02C7/224

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. The system includes a fuel air heat exchanger with a fuel passage that is in thermal contact with an engine cooling air passage. The system further includes a fuel deoxygenator located upstream of the fuel air heat exchanger and configured to deliver deoxygenated fuel to the fuel air heat exchanger fuel passage. The system also includes a valve configured to moderate engine cooling air flow to the engine cooling air passage.

公开(公告)号：US10371094B2

公开(公告)日：2019-08-06

申请号：US14789643

申请日：2015-07-01

Applicant: ROLLS-ROYCE PLC

Inventor： Andrew Martin Rolt

IPC: F02K1/08 ,  F02K1/09 ,  F02K3/02 ,  F01D17/14 ,  F02K1/15 ,  F02K1/48 ,  F02K3/075 ,  F02C3/04 ,  F02K3/06

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.

公开(公告)号：US09376213B2

公开(公告)日：2016-06-28

申请号：US13644900

申请日：2012-10-04

Applicant: ROLLS-ROYCE PLC

Inventor： Andrew Martin Rolt

IPC: B64D27/24 ,  B64D27/02

CPC classification number: B64D27/24 ,  B64D27/02 ,  Y02T50/62

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。

公开(公告)号：US09266617B2

公开(公告)日：2016-02-23

申请号：US13644509

申请日：2012-10-04

Applicant: ROLLS-ROYCE PLC

Inventor： Betka Rebhi ,  Lorenzo Raffaelli ,  Andrew Martin Rolt

IPC: B64D27/02

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。