公开(公告)号：US10944285B2

公开(公告)日：2021-03-09

申请号：US16813267

申请日：2020-03-09

Applicant: Rolls-Royce plc

Inventor： Lorenzo Raffaelli ,  Richard J. Tunstall

IPC: H02J7/14 ,  H02J4/00 ,  F01D15/10 ,  H02J7/34 ,  B60L1/00 ,  H02J3/00

Abstract: Apparatus for controlling a power generation system, the apparatus comprising a controller configured to: identify a trigger indicative of a future change in electrical power output by the power generation system to a first power level; control the power generation system to change electrical power output to a second power level in response to the trigger, the second power level being equal to, or different to the first power level; and control supply of at least a portion of the electrical power output from the power generation system at the second power level to an electrical energy storage system to charge the electrical energy storage system.

公开(公告)号：US08857760B2

公开(公告)日：2014-10-14

申请号：US13644980

申请日：2012-10-04

Applicant: Rolls-Royce PLC

Inventor： Stephen Geoffrey Brown ,  Lorenzo Raffaelli

IPC: B64D33/02 ,  B64D29/00 ,  B64D29/06 ,  B64D29/02 ,  B64C11/00

CPC classification number: B64C11/001 ,  B64D29/02 ,  B64D33/02 ,  B64D33/04 ,  F02C7/042 ,  F02K1/09 ,  F02K1/12 ,  F02K5/00

Abstract: This invention relates to a propulsive unit for an aircraft, comprising: a nacelle which defines a duct for channeling an airflow when in use and which provides an outwardly facing surface of the propulsive unit, the outwardly facing surface having an aerodynamic shape; a fan unit for accelerating the airflow within the duct when in use; wherein the duct has an inlet and an outlet and the nacelle is operable to adjust the either or both of the area of the inlet and outlet while substantially retaining the aerodynamic shape of the outwardly facing surface.

Abstract translation: 本发明涉及一种用于飞行器的推进单元，包括：机舱，其限定用于在使用时引导气流并且提供推进单元的面向外的表面的管道，面向外的表面具有空气动力学形状; 风扇单元，用于在使用时加速管道内的气流; 其中所述管道具有入口和出口，并且所述机舱可操作以调节所述入口和出口的所述区域中的一个或两者，同时基本上保持面向外的表面的空气动力学形状。

公开(公告)号：US10167084B2

公开(公告)日：2019-01-01

申请号：US14830143

申请日：2015-08-19

Applicant: ROLLS-ROYCE PLC

Inventor： Rory D Stieger ,  Lorenzo Raffaelli

IPC: B64D13/08 ,  B64D13/06 ,  B64C21/06 ,  B64D33/02

Abstract: An air duct arrangement (58) for an aircraft (40). The arrangement (58) comprises an environmental control system (ECS) (50). The ECS (50) comprises an air inlet (60) arranged to ingest a low velocity portion of a boundary layer flow adjacent the aircraft fuselage (44), and to deliver a flow of air to an environmental control system air intake (66). The arrangement (58) further comprises an ejector (70) arranged to receive an ECS exhaust (76), and boundary layer air from an aft region of the aircraft (40), and to exhaust air to the ambient airstream at an aft portion of the aircraft (40).

公开(公告)号：US10337330B2

公开(公告)日：2019-07-02

申请号：US15227714

申请日：2016-08-03

Applicant: ROLLS-ROYCE plc

Inventor： Bryce D Conduit ,  Lorenzo Raffaelli

IPC: F01D5/02

Abstract: A method of assembling a rotor stack comprising a plurality of component parts, the method comprising: determining swash measurements for interfacing surfaces of the plurality of parts; calculating a runout estimate for a plurality of relative orientations of the parts; applying an optimization algorithm to identify an optimal orientation from the plurality of relative orientations based on the runout estimates; and assembling the parts in the optimal orientation.

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。