公开(公告)号：US11713105B2

公开(公告)日：2023-08-01

申请号：US17344248

申请日：2021-06-10

Applicant: ROLLS-ROYCE plc

Inventor： Matthew Moxon

IPC: B64C3/32 ,  B64C3/14 ,  B64D27/24 ,  B64D27/02 ,  B64C3/38 ,  B60L50/70 ,  B60L50/40

CPC classification number: B64C3/32 ,  B64C3/14 ,  B64C3/38 ,  B64D27/24 ,  B60L50/40 ,  B60L50/70 ,  B60L2200/10 ,  B64D2027/026

Abstract: An aircraft comprising a wing having a spanwise lift distribution extending from a root to a tip, the lift distribution defining an inboard region defining a positive lift contribution, an outboard region defining a negative lift contribution, and an intermediate region defining a neutral lift contribution, the neutral region being spaced from the tip and from the root. A propulsion system is provided, comprising a wing mounted propulsor. The wing mounted propulsor has a rotational axis (x) positioned substantially at a span of the wing where a value of δLift/δSpan is at a maximum for the span of the wing, and may be located at the intermediate region along the span of the wing.

公开(公告)号：US10787270B2

公开(公告)日：2020-09-29

申请号：US15899481

申请日：2018-02-20

Applicant: ROLLS-ROYCE plc

Inventor： Martin N. Goodhand ,  Matthew Moxon

IPC: B64D27/02 ,  B64C11/18 ,  B64C11/48 ,  B64C21/00

Abstract: A boundary layer propulsor comprises a rotor and a plurality of first aerofoil blades. The rotor has an axis of rotation. The plurality of first aerofoil blades extends radially from the rotor and is arranged in a circumferential array around the axis of rotation. Each of the first aerofoil blades has, in a radially outward sequence, a radially proximal portion, a middle portion, and a radially distal portion. The radially proximal portion has a first cambered cross-section, the middle portion has a second uncambered cross-section, and the radially distal portion has a third cambered cross-section. The first cambered cross-section is cambered in an opposite sense to the third cambered cross-section.

公开(公告)号：US10414484B2

公开(公告)日：2019-09-17

申请号：US14854380

申请日：2015-09-15

Applicant: ROLLS-ROYCE plc

Inventor： Matthew Moxon

IPC: B64C11/00 ,  B64C3/38 ,  B64C3/52 ,  B64C29/00 ,  B64C11/46 ,  B64D45/00

Abstract: An aircraft (40). The aircraft comprises a plurality of propellers (46) mounted to wings (44). Each propeller comprises at least one blade (72, 74) coupled to a respective propeller cyclic actuator (78) configured to cyclically alter the pitch of the respective blade (72, 74) as the propeller rotates. The aircraft (40) is configured such that provision of cyclic pitch to the propeller (46) twists at least a portion of the wing (44) about a span of the wing (46) relative to the fuselage (42), to thereby adjust the local angle of incidence of the wing (46).

公开(公告)号：US10358933B2

公开(公告)日：2019-07-23

申请号：US15692619

申请日：2017-08-31

Applicant: ROLLS-ROYCE PLC

Inventor： Matthew Moxon

IPC: F01D11/24 ,  F04D27/02 ,  F04D27/00 ,  F01D17/14

Abstract: A method of controlling a rotor tip clearance in a gas turbine engine (10). The method comprises determining an engine or component remaining useful life Tr, and controlling a tip clearance control arrangement (38) to maintain a rotor tip clearance (36) at a target tip clearance Dtarget. The target tip clearance Dtarget is determined in accordance with a function of remaining engine life Tr.

公开(公告)号：US10358229B2

公开(公告)日：2019-07-23

申请号：US15135040

申请日：2016-04-21

Applicant: ROLLS-ROYCE plc

Inventor： Matthew Moxon

IPC: B64D33/02 ,  B64C15/00 ,  B64C21/00 ,  B64D27/02 ,  B64C3/50 ,  B64C11/00 ,  B64D27/10 ,  B64D27/24 ,  B64D29/04 ,  B64D33/04

Abstract: An aircraft including trailing edge flaps, a wing mounted propulsor positioned such that the flaps are located in a slipstream of the first propulsor in use when deployed. The aircraft further including a thrust vectorable propulsor configured to selectively vary the exhaust efflux vector of the propulsor in at least one plane. The thrust vectorable propulsor includes a ducted fan configurable between a first mode, in which the fan provides net forward thrust to the aircraft, and a second mode in which the fan provides net drag to the aircraft. The fan is positioned to ingest a boundary layer airflow in use when operating in the first mode.

公开(公告)号：US09994330B2

公开(公告)日：2018-06-12

申请号：US15793529

申请日：2017-10-25

Applicant: ROLLS-ROYCE plc

Inventor： Matthew Moxon

IPC: B64D27/10 ,  B64D27/14 ,  B64C39/10 ,  B64D27/02

CPC classification number: B64D27/10 ,  B64C39/10 ,  B64C2039/105 ,  B64D27/02 ,  B64D27/14

Abstract: An aircraft comprises at least first and second gas turbine engines arranged in a line extending generally normally to an aircraft longitudinal axis (A), each engine comprising at least one compressor or turbine rotor disc defining a respective rotational plane (D32-D42). The rotational plane (D32-D42) of at least one of the rotors of at least one of the engines is angled relative to the aircraft longitudinal line (A) such that a burst disc plane of the respective engine is nonintersecting with another engine.