公开(公告)号：US11415014B2

公开(公告)日：2022-08-16

申请号：US17170339

申请日：2021-02-08

Applicant: Rolls-Royce plc ,  Rolls-Royce Corporation

Inventor： Michael J. Whittle ,  Daniel K. Vetters ,  Jeffrey A. Walston ,  Eric Koenig

IPC: F01D9/04 ,  F01D5/28

Abstract: The present disclosure is related to turbine vane assemblies comprising ceramic matrix composite materials. The turbine vane assemblies further including reinforcements that strengthen joints in the turbine vane assemblies.

公开(公告)号：US11414198B2

公开(公告)日：2022-08-16

申请号：US16546362

申请日：2019-08-21

Applicant: ROLLS-ROYCE plc

Inventor： Giles E. Harvey

IPC: H02K9/19 ,  H02K7/14 ,  B64D27/24 ,  B64C29/00

Abstract: An aircraft propulsion system comprises a vertical lift propulsor mounted within a wing of the aircraft. The vertical propulsor comprises an electric motor comprising a rotor mounted to a plurality of propulsor blades, the motor further comprising a stator. The rotor is provided radially outwardly of the stator.

公开(公告)号：US11408428B2

公开(公告)日：2022-08-09

申请号：US17174967

申请日：2021-02-12

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 a turbine, compressor, and core shaft connecting turbine to compressor; a fan located upstream of the engine core and including a plurality of fan blades each having a leading and trailing edge. The turbine includes a lowest pressure turbine stage having a row of rotor blades, each rotor blades extending radially and having a leading and trailing edge. The engine has a fan tip axis that joins a radially outer tip of the leading edge of a fan blade and the radially outer tip of the trailing edge of a rotor blade of the lowest pressure stage. The fan tip axis lies in a longitudinal plane which contains a centreline of engine. A fan axis angle is defined as the angle between fan tip axis and centreline, and is in a range between 10 and 20 degrees.

公开(公告)号：US11408345B2

公开(公告)日：2022-08-09

申请号：US16555212

申请日：2019-08-29

Applicant: Rolls-Royce Corporation ,  Rolls-Royce plc

Inventor： Isabelle Erickson ,  Adam L. Kempers ,  David Edwards ,  John Gebhard ,  Jeremy Gallagher

IPC: F02C7/14 ,  F01D25/20 ,  F02C7/32 ,  F02C7/36 ,  F16H57/04 ,  F16H57/08

Abstract: An oil delivery system is provided that includes a tank for a gas turbine engine, where the tank is positioned radially outward from a compressor section, a combustor section, and/or a turbine section of the gas turbine engine. The tank is configured to store oil for the gas turbine engine. The oil delivery system further includes a primary lubrication system including a sump of a power gearbox, a pump, and an oil feed line. The oil feed line extends from the tank to the primary lubrication system. The oil feed line is configured to allow a flow of oil to pass from the tank to the pump and from the pump through the power gearbox to the sump of the power gearbox.

公开(公告)号：US11407517B2

公开(公告)日：2022-08-09

申请号：US16394280

申请日：2019-04-25

Applicant: ROLLS-ROYCE plc

Inventor： David P Scothern

IPC: B64D27/12 ,  B64D27/24 ,  F01D15/10 ,  F02C6/20 ,  B64D27/02

Abstract: A hybrid aircraft propulsion system. The system comprises a gas turbine engine comprising a compressor, a combustor, one or more turbines, a shaft coupled to one of the turbines, and a bypass fan mechanically driven by the shaft. The system further comprises an electrical generator mechanically coupled to the shaft, and an auxiliary propulsor mechanically coupled to an electric motor and electrically coupled to the electric generator. At maximum power, the gas turbine engine is configured to produce a turbine entry temperature at maximum power between 1800 Kelvin and 2000 Kelvin, the engine comprises a fan bypass ratio of between 4:1 and 13:1, and the generator is configured to absorb between 10% and 60% of the mechanical power generated by the turbine.

公开(公告)号：US11383853B2

公开(公告)日：2022-07-12

申请号：US16437263

申请日：2019-06-11

Applicant: ROLLS-ROYCE plc

Inventor： Richard Peace ,  Adam Newman

IPC: B64D33/08 ,  B64D27/24 ,  F04D29/58 ,  F04D25/08 ,  B64D33/02

Abstract: An electric propulsion unit (102) for an aircraft is shown. A fan (202) produces a pressured airflow (P) by raising the pressure of an incident airflow (I). An electric machine (201) is arranged to drive the fan and is located within a casing (204). A primary cooling circuit (205) is located within the casing, and includes the electric machine and a first pass of a fluid-fluid heat exchanger (208), thereby placing the electric machine and the fluid-fluid heat exchanger in thermal communication. A secondary cooling circuit includes a second pass of the fluid-fluid heat exchanger and an air-fluid heat exchanger (210) located within the pressurised airflow produced by the fan, thereby placing the fluid-fluid heat exchanger and the air-fluid heat exchanger in thermal communication.

公开(公告)号：US11381190B2

公开(公告)日：2022-07-05

申请号：US17140538

申请日：2021-01-04

Applicant: ROLLS-ROYCE plc

Inventor： Jishnu K Kambrath ,  Xiong Liu ,  Youyi Wang ,  Aaron A Ayu

IPC: H02P1/46 ,  H02P23/04 ,  B63H21/17 ,  B64D31/06 ,  B64D35/02 ,  H02P23/14 ,  H02P27/06

Abstract: A torsional mode damping controller in which the controller modifies electrical power to an electrical motor to provide active damping control of torsional vibration in rotating masses. The controller receives a measurement of a rotational speed of the rotating masses ωm and an estimate or a measurement of a torque transmitted between the rotating masses Tsh; based on the received transmitted torque Tsh, generate a compensating torque to suppress vibration Tcom; based on the received rotational speed ωm and the compensating torque Tcom, generate an electromagnetic torque modification signal Tmodi; and modify the electrical power provided to the electrical motor on the basis of the electromagnetic torque modification signal Tmodi. The controller is further configured to generate compensating torque Tcom by applying a filter to the received transmitted torque Tsh, based on plural tunable parameters including a tuning gain K, a cut-off frequency ωn and a resonant damping ratio ζ.

公开(公告)号：US11371381B2

公开(公告)日：2022-06-28

申请号：US16747695

申请日：2020-01-21

Applicant: ROLLS-ROYCE plc

Inventor： Laura E Wood ,  Julius K Listianto ,  Kareem W Rodgers ,  Dominic J Anelli

IPC: F01D21/00 ,  F02C7/36 ,  G01D5/14 ,  G01D5/244

Abstract: A monitoring system includes first and second, axially adjacent, phonic wheels formed from respective axially adjacent portions of a unitary annular body and mounted coaxially to the shaft for rotation therewith. The first and second phonic wheels have respective first and second circumferential rows of teeth. The system further includes a sensor configured to detect the passage of the first row of teeth by generating a first alternating measurement signal component, and to detect the passage of the second row of teeth by generating a second alternating measurement signal component. The sensor generates a signal having both the first and the second alternating measurement signal components when axially positioned midway between the first and second phonic wheels. The teeth of the first and second rows are configured such that the first alternating measurement signal component has an identical frequency to the second alternating measurement signal component.

公开(公告)号：US20220197009A1

公开(公告)日：2022-06-23

申请号：US17645413

申请日：2021-12-21

Applicant: Rolls-Royce plc

Inventor： Rory Williams ,  Joanna Tomlin ,  Matthew Calder ,  Aditya Banerjee ,  Daniel Matthew Gillians ,  Benedick James Loudon von Bertele

IPC: G02B23/24 ,  G06T19/00 ,  G06F3/01

Abstract: A borescope feedback system with haptic feedback includes a borescope cable, a containment device, a cable sensor that is configured to detect motion of the borescope cable and output cable sensor data indicative of the motion of the borescope cable, a feedback device that is configured to controllably apply friction to the borescope cable, and a computing device configured to output a graphical user interface of a virtual reality representation of the borescope cable in a virtual environment; determine at least one of a direction of axial motion, a direction of circumferential motion, or a magnitude of the motion of the borescope cable; determine a collision of the virtual reality representation of the distal portion of the borescope cable with an obstruction in the virtual environment; and output a feedback signal to the feedback device that causes the feedback device to apply an amount of friction to the borescope cable.

公开(公告)号：US20220186381A1

公开(公告)日：2022-06-16

申请号：US17551480

申请日：2021-12-15

Applicant: Rolls-Royce Corporation ,  Rolls-Royce plc

Inventor： Quinlan Yee Shuck ,  Scott Nelson ,  Martyn Anthony Jones ,  Peter E. Daum

IPC: C23C24/04 ,  B33Y10/00 ,  B33Y40/10 ,  B33Y70/00

Abstract: A method may include cold spraying a masking material on selected locations of a component to form a masking layer, wherein the masking material comprises a metal or alloy; additively manufacturing an additively manufactured portion of the component at locations at which the masking layer is not present; and removing the masking layer from the component. The masking layer may be configured to protect portions of the component by covering or otherwise providing a physical barrier that reduces or prevents material from adhering to unwanted portions of the component during a subsequent manufacturing and/or repair technique. Additionally, the masking layer may be reflective to infrared radiation and/or intimately contact the component and function as a heat sink or thermally conductive layer to transfer heat from the component.