公开(公告)号：US11286784B2

公开(公告)日：2022-03-29

申请号：US17149128

申请日：2021-01-14

Applicant: ROLLS-ROYCE PLC

Inventor： Soumyik Bhaumik ,  Rohit Chouhan

IPC: F01D5/14

Abstract: An aerofoil assembly includes a platform and one or more aerofoils extending radially outward from the platform. The platform has a first edge, a second edge, and a platform surface disposed between the first edge and the second edge. The one or more aerofoils are disposed between the first edge and the second edge. Each of the one or more aerofoils has a leading edge proximal to the first edge and a trailing edge distal to the first edge. The platform defines one or more recesses disposed between the leading edge of each of the one or more aerofoils and the first edge.

公开(公告)号：US20220090541A1

公开(公告)日：2022-03-24

申请号：US17544660

申请日：2021-12-07

Applicant: ROLLS-ROYCE plc

Inventor： Mark SPRUCE

IPC: F02C7/36 ,  F16H1/28 ,  F16H57/08

Abstract: An engine core including a turbine, compressor, and a core shaft connecting the turbine and compressor; a fan located upstream of the engine core including a plurality of fan blades; and a gearbox. The gearbox is arranged to receive an input from the core shaft and to output drive to the fan to drive the fan at a lower rotational speed than the core shaft. The gearbox is an epicyclic gearbox and includes a sun gear, a plurality of planet gears, ring gear, and planet carrier to the mounted planet gears. The planet carrier has an effective linear torsional stiffness and the gearbox has a gear mesh stiffness between the planet gears and the ring gear. A carrier to ring mesh ratio of: the ⁢ ⁢ effective ⁢ ⁢ linear ⁢ ⁢ torsional stiffness ⁢ ⁢ of ⁢ ⁢ the ⁢ ⁢ planet ⁢ ⁢ carrier ⁢ gear ⁢ ⁢ mesh ⁢ ⁢ stiffness ⁢ ⁢ between ⁢ ⁢ the ⁢ ⁢ planet ⁢ ⁢ gears ⁢ ⁢ and ⁢ ⁢ the ⁢ ⁢ ring ⁢ ⁢ gear is greater than or equal to 0.2.

公开(公告)号：US20220090502A1

公开(公告)日：2022-03-24

申请号：US17464047

申请日：2021-09-01

Applicant: ROLLS-ROYCE plc

Inventor： Bharat M. LAD

IPC: F01D5/14

Abstract: An aircraft engine having a turbine, the turbine having at least one flutter-resistant blade, the blade having a leading edge (LE), a trailing edge (TE), a midchord (MC), a minimum radial height rhub, a maximum radial height rtip, and a radial extent between rhub and rtip, wherein, at every point along the radial extent of the blade, the blade has a modeshape value V1 for a blade first vibratory mode defined as V 1 =  D 1 ⁢ LE   D 1 ⁢ MC  , and wherein, when the engine is operating between its maximum speed and 70% of that maximum speed, at least 80% of the radial extent of the blade has a modeshape value V1 from 0 to 1.5.

公开(公告)号：US11274729B2

公开(公告)日：2022-03-15

申请号：US16515730

申请日：2019-07-18

Applicant: Rolls-Royce plc

Inventor： Mark Spruce

IPC: F02C7/36 ,  F02K3/06 ,  F16H1/02 ,  F16H55/08 ,  F16H1/06 ,  F16H55/17

Abstract: A gas turbine engine includes an engine core, a fan and a gearbox interconnecting the engine core and the fan. The engine core is configured to drive rotation of at least one shaft. The power gearbox is configured to transfer torque from the at least one shaft to an output shaft at a reduced rotational speed. The output shaft is coupled to the fan to drive the fan at the reduced speed and provide trust for the gas turbine engine.

公开(公告)号：US20220056916A1

公开(公告)日：2022-02-24

申请号：US17520126

申请日：2021-11-05

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 having a core length and comprising 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; and 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, wherein a ratio of the fan tip radius to the turbine diameter at the lowest pressure rotor stage is in a range from 1.2 to 2.0; and wherein the engine core length is in a range from 150 cm to 320 cm.

公开(公告)号：US20220056852A1

公开(公告)日：2022-02-24

申请号：US17378243

申请日：2021-07-16

Applicant: ROLLS-ROYCE plc

Inventor： Mark SPRUCE

IPC: F02C7/36 ,  F16H1/28

Abstract: A gas turbine engine for an aircraft configured with an engine core that has a turbine, a compressor, and a core shaft connecting the turbine to the compressor. A fan located upstream of the engine core, that has a plurality of fan blades. A gearbox arranged to receive an input from the core shaft and to output to the fan so as to drive the fan at a lower rotational speed than the core shaft. The gearbox being an epicyclic gearbox having a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted. The gearbox having an overall gear mesh stiffness, and wherein the overall gear mesh stiffness of the gearbox is greater than or equal to 1.05×109 N/m and less than or equal to 8.0×109 N/m.

公开(公告)号：US11248467B2

公开(公告)日：2022-02-15

申请号：US16743601

申请日：2020-01-15

Applicant: ROLLS-ROYCE plc

Inventor： Nicholas M Merriman

IPC: F01D5/14

Abstract: A fan blade comprising a tip surface configured in use to face an internal wall of a nacelle. The tip surface having a suction side edge, a pressure side edge and a chamfer such that in use the suction side edge is further than the pressure side edge from the internal wall of the nacelle. The chamfer angle of the chamfer varies along the tip surface between a leading edge of the fan blade and a trailing edge of the fan blade.

公开(公告)号：US11242155B2

公开(公告)日：2022-02-08

申请号：US16437284

申请日：2019-06-11

Applicant: ROLLS-ROYCE plc

Inventor： Gareth M Armstrong ,  Nicholas Howarth

IPC: B64D27/10 ,  F02C3/06 ,  F02K3/06 ,  F02K3/068 ,  F02C3/04 ,  F01D5/28 ,  F02C7/04 ,  F02C3/107 ,  B64D33/02

Abstract: A gas turbine engine has a compression system radius ratio defined as the ratio of the radius of the tip of a fan blade to the radius of the tip of the most downstream compressor blade in the range of from 5 to 9. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.

公开(公告)号：US11230941B2

公开(公告)日：2022-01-25

申请号：US16914911

申请日：2020-06-29

Applicant: ROLLS-ROYCE plc

Inventor： Jonathan P Bradley

IPC: F01D15/10 ,  F01D25/16

Abstract: An aircraft gas turbine engine (10) comprises a main engine spool (22) and a bearing arrangement (36) configured to rotatably support the main engine spool (22). The bearing arrangement (36) includes a damper (41) comprising a static element (42) and a moveable element (39). The gas turbine engine further comprises an electric machine (30) comprising a rotor (34) and a stator (32). The rotor (34) is mounted to the main engine spool (22), and the stator (32) is mounted to the moveable element (39) of the damper to be moveable with the moveable element (39).

公开(公告)号：US20220019558A1

公开(公告)日：2022-01-20

申请号：US17333868

申请日：2021-05-28

Applicant: ROLLS-ROYCE plc

Inventor： Nigel T. HART ,  Raza SEKHA

IPC: G06F16/18 ,  G07C5/00

Abstract: A computer-implemented method of creating a database of characterising codes, each characterising code being indicative of character of a respective example of a physical system. The method comprises the steps of performing for each example: (a) receiving data including respective values of a plurality of parameters associated with the system; (b) identifying, from a plurality of data clusters, a data cluster for each value, said data clusters each defining a range of possible values of the respective parameter; (c) assigning each parameter to its identified data cluster; (d) generating, from the assigned data clusters, a characterising code for that example including a unique label for each of the identified data clusters; and (e) storing the characterising code in a database of characterising codes.