公开(公告)号：US11215295B2

公开(公告)日：2022-01-04

申请号：US16580046

申请日：2019-09-24

Applicant: ROLLS-ROYCE plc

Inventor： Christopher A. Murray

IPC: F16K49/00 ,  F02M53/08 ,  F16K31/04

Abstract: A controller assembly comprises an electromechanical actuator and a single-stage pneumatic flow switch configured to thermally protect the electromechanical actuator by a supply of cooling fluid. The single-stage pneumatic flow switch is movable between a first mode in which the switch is configured to open a cooling fluid flow passage and a second mode in which the switch is configured to close the cooling fluid flow passage. The electromechanical actuator is coupled to a valve movable between an open and a closed configuration.

公开(公告)号：US20210404346A1

公开(公告)日：2021-12-30

申请号：US17147910

申请日：2021-01-13

Applicant: Rolls-Royce plc

Inventor： Ricardo Pelin

IPC: F01D21/04 ,  F01D25/00 ,  F01D25/24 ,  B33Y80/00

Abstract: A fan track liner for a fan containment arrangement for a gas turbine includes a cellular impact structure and a supporting sub-laminate integrally formed with each other from fibre-reinforced material. The fan track liner further includes a ballistic barrier comprising a woven reinforcing fibre ply and a layer of reinforcing fibre felt. There is also disclosed an associated fan containment arrangement and a method of manufacturing a fan track liner.

公开(公告)号：US11204037B2

公开(公告)日：2021-12-21

申请号：US17338159

申请日：2021-06-03

Applicant: ROLLS-ROYCE plc

Inventor： Richard G Stretton ,  Michael C Willmot

IPC: F04D19/00 ,  F01D5/12

Abstract: A gas turbine engine for an aircraft includes an engine core including an engine core, a turbine, a compressor, and a core shaft connecting the turbine to the compressor, the turbine comprising a lowest pressure rotor stage, the turbine having a turbine diameter at the lowest pressure rotor stage. A fan located upstream of the engine core, the fan comprising a plurality of fan blades extending from a hub, the hub and fan blades together defining a fan face having a fan face area and a fan tip radius. A ratio of the fan tip radius to the turbine diameter at the lowest pressure rotor stage is in the range from 1.2 to 2.0.

公开(公告)号：US20210388726A1

公开(公告)日：2021-12-16

申请号：US17286327

申请日：2019-09-30

Applicant: Rolls-Royce plc

Inventor： David Churcher ,  Andrew R. Collis

IPC: F01D5/14 ,  B29C65/70

Abstract: A method of manufacturing a component for a gas turbine engine includes applying a thermoplastic polymer sheet over a composite body for the component; applying a shield over part of the composite body, the shield terminating at an end which overlies the thermoplastic polymer sheet and defines an interface between shielded and unshielded regions of the component; and pressing the shield into the thermoplastic polymer sheet so that the thermoplastic polymer sheet deforms around the end of the shield, such that the exterior profile of the component at the interface between the shielded and unshielded regions is flush.

公开(公告)号：US20210381430A1

公开(公告)日：2021-12-09

申请号：US17331020

申请日：2021-05-26

Applicant: ROLLS-ROYCE PLC

Inventor： Matthew SILVESTER ,  Geoffrey HUGHES

IPC: F02C3/073 ,  B64D27/10 ,  F04D25/02

Abstract: A gas turbine engine for an aircraft includes a fan system having a reverse travelling wave first flap mode, Fan RTW, and including a fan located upstream of the engine core; a fan shaft; and a front engine structure arranged to support the fan shaft and having a front engine structure nodding mode comprising a pair of modes at similar, but not equal, natural frequencies in orthogonal directions; and a gearbox. An LP rotor system including the fan system and a gearbox output shaft arranged to drive the fan shaft has a first reverse whirl rotor dynamic mode, Rotor RW, and a first forward whirl rotor dynamic mode, 1FW. The engine has a maximum take-off speed, MTO. A backward whirl frequency margin of: the ⁢ ⁢ lowest ⁢ ⁢ frequency ⁢ ⁢ of ⁢ ⁢ either ⁢ ⁢ mode ⁢ ⁢ Fan ⁢ ⁢ RTW ⁢ ⁢ or ⁢ ⁢ Rotor ⁢ ⁢ RW ⁢ ⁢ at the ⁢ ⁢ MTO ⁢ ⁢ speed the ⁢ ⁢ MTO ⁢ ⁢ speed may be in the range from 15 to 50%.

公开(公告)号：US11196320B2

公开(公告)日：2021-12-07

申请号：US16690510

申请日：2019-11-21

Applicant: Rolls-Royce plc ,  Rolls-Royce Corporation

Inventor： Mark Boden ,  Donald Klemen ,  Jonathan Terrell ,  Brian Maners

IPC: H02K5/15 ,  H02K7/00 ,  H02K5/22 ,  H02K1/27

Abstract: A rotor of an electric machine includes a main rotor body having a longitudinal axis, the main rotor body comprising: a hollow cylinder body with a first end and a second end; an integral end flange at the first end; a separate end flange disposed at the second end of the cylinder body; and laminations disposed on an outer surface of the cylinder body, the laminations comprising magnetic material.

公开(公告)号：US11193381B2

公开(公告)日：2021-12-07

申请号：US16415196

申请日：2019-05-17

Applicant: Rolls-Royce plc

Inventor： Michael J. Whittle

IPC: F01D9/02 ,  F01D9/04 ,  F01D5/18 ,  F01D5/28

Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a spar, a turbine vane, and load transfer pins. The spar comprises metallic materials and is configured to support other components of the turbine vane assembly relative to an associated turbine case. The turbine vane comprises ceramic matrix composite materials and is shaped to include an airfoil configured to direct the flow of hot gasses through a primary gas path of the turbine vane assembly.

公开(公告)号：US11189398B2

公开(公告)日：2021-11-30

申请号：US16734491

申请日：2020-01-06

Applicant: ROLLS-ROYCE plc

Inventor： Chloe J. Palmer

IPC: H01B12/00 ,  H01B12/16 ,  H01B12/02 ,  H02K3/50 ,  H02K9/20 ,  H02K11/04 ,  H02K55/04

Abstract: A superconducting electrical power distribution system has a superconducting bus bar and one or more bus bar thermal conductor lines extending in thermal proximity along the bus bar to receive heat from the bus bar over the length of the bus bar. The system further has superconducting cables electrically connected to the bus bar at respective electrical joints distributed along the bus bar. The system further has a cryogenic cooling sub-system. The system further has a network comprising first and second thermal conductor lines, each line comprising a cold end which is cooled by the cryogenic cooling sub-system, and an opposite hot end, whereby heat received by each line is normally conducted along the line in a direction from its hot end to its cold end.

公开(公告)号：US11181042B2

公开(公告)日：2021-11-23

申请号：US16411347

申请日：2019-05-14

Applicant: ROLLS-ROYCE plc

Inventor： Michael O Hales ,  Craig W Bemment ,  Stephane M M Baralon ,  Benjamin J Sellers ,  Christopher Benson ,  Benedict R Phelps ,  Mark J Wilson

IPC: F02C3/073 ,  F02C7/36

Abstract: A gas turbine engine has a cycle operability parameter β in a defined range to achieve improved overall performance, taking into account fan operability and/or bird strike requirements as well as engine efficiency. The defined range of cycle operability parameter β may be particularly beneficial for gas turbine engines in which the fan is driven by a turbine through a gearbox.

公开(公告)号：US20210355843A1

公开(公告)日：2021-11-18

申请号：US17231460

申请日：2021-04-15

Applicant: ROLLS-ROYCE plc

Inventor： Fernando L. TEJERO EMBUENA ,  David G. MACMANUS ,  Christopher TJ. SHEAF

IPC: F01D25/24

Abstract: A nacelle for a gas turbine engine includes a leading edge, a trailing edge and a longitudinal centre line along a length of the nacelle. A highlight radius (rhi) is defined as a radial distance between the longitudinal centre line and the leading edge. A trailing edge radius (rte) is defined as a radial distance between the longitudinal centre line and the trailing edge. A nacelle length (Lnac) is defined as an axial distance between the leading edge and the trailing edge. A ratio between the nacelle length (Lnac) and the highlight radius (rhi) is defined as R1 (Lnac/rhi). The ratio R1 is greater than or equal to 2.4 and less than or equal to 3.2. A ratio between the trailing edge radius (rte) and the highlight radius (rhi) is defined as R2. The ratio R2 is greater than or equal to 0.89 and less than or equal to 1.