-
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
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
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
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
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
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.
-
Patent Agency Ranking
公开(公告)号：US11358307B2
公开(公告)日：2022-06-14
申请号：US16090963
申请日：2017-03-28
Applicant: ROLLS-ROYCE PLC
Inventor： Giovanni Antonio Marengo
Abstract: There is disclosed a method of manufacturing a composite component comprising a main body and an integral flange, the method comprising applying fibre-reinforcement material on a tool having a main body portion and a flange-forming portion to provide a pre-form comprising a body region and a longitudinally adjacent flange region. The pre-form extends generally longitudinally between two longitudinal ends; and a trailing ply of the pre-form extends generally longitudinally between the longitudinal end closest to the flange region and an inner ply end located in the flange region or partway into the body region. Relative movement between the flange-forming portion and the main body portion causes sliding movement between the trailing ply and the flange-forming portion during a flange forming operation, thereby causing a tension force in at least the flange region of the pre-form of during forming of the flange.
-
公开(公告)号：US20220178543A1
公开(公告)日：2022-06-09
申请号：US17550630
申请日：2021-12-14
Applicant: ROLLS-ROYCE plc , ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
Inventor： Luca TENTORIO , Imon-Kalyan BAGCHI
Abstract: A lean burn combustor includes a plurality of lean burn fuel injectors, each including a fuel feed arm and a lean burn fuel injector head with a lean burn fuel injector head tip, wherein the lean burn fuel injector head tip has a lean burn fuel injector head tip diameter, the lean burn fuel injector head including a pilot fuel injector and a main fuel injector, the main fuel injector being arranged coaxially and radially outwards of the pilot fuel injector; and a combustor chamber extending along an axial direction for a length and including a radially inner annular wall, a radially outer annular wall, and a meter panel defining the size and shape of the combustor chamber, wherein the combustor chamber includes primary and secondary combustion zones. A ratio of the combustor chamber length to the lean burn fuel injector head tip diameter is less than 5.
-
公开(公告)号：US20220178541A1
公开(公告)日：2022-06-09
申请号：US17367952
申请日：2021-07-06
Applicant: ROLLS-ROYCE PLC , ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
Inventor： Luca TENTORIO , Imon-Kalyan BAGCHI
Abstract: A lean burn combustor includes a plurality of lean burn fuel injectors, each including a fuel feed arm and a lean burn fuel injector head with a lean burn fuel injector head tip, wherein the tip has a lean burn fuel injector head tip diameter, the lean burn fuel injector head including a pilot fuel injector and a main fuel injector, the main fuel injector being arranged coaxially and radially outwards of the pilot fuel injector; and a combustor chamber extending along an axial direction and including a radially inner annular wall, a radially outer annular wall, and a meter panel defining the size and shape of the combustor chamber, which includes a primary combustion zone with a primary combustion zone depth and a secondary combustion zone. A ratio of the primary combustion zone depth to the lean burn fuel injector head tip diameter is less than 2.4.
-
公开(公告)号：US20220162953A1
公开(公告)日：2022-05-26
申请号：US17514977
申请日：2021-10-29
Applicant: ROLLS-ROYCE plc
Inventor： Geoffrey B JONES , Edward J SPALTON , Duncan A MACDOUGALL
IPC: F01D9/04
Abstract: A gas turbine engine includes: a fan rotating about an engine main axis; a core duct; an engine core; an Engine Section Stator (ESS) including a plurality of ESS vanes and arranged in the core duct downstream of the fan; and a plurality of variable inlet guide vanes (VIGV) adapted to rotate about a pivot axis and arranged in the core duct downstream of the ESS. The VIGV vanes are arranged angularly rotated with respect to the ESS vanes such that the VIGVs are shielded by the ESS, thereby protecting the VIGVs from icing and from ice shedding from the ESS vanes.
-
公开(公告)号：US11339714B2
公开(公告)日：2022-05-24
申请号：US17061057
申请日：2020-10-01
Applicant: ROLLS-ROYCE plc , ROLLS-ROYCE CORPORATION
Inventor： Rory D Stieger , Daniel Swain
Abstract: A gas turbine engine comprises, in fluid flow series, a gas-generator compressor, a combustor, a gas-generator turbine, and a free power turbine. The gas-generator compressor is an axi-centrifugal compressor comprising a plurality of axial compression stages followed by a single centrifugal compression stage, wherein the International Standard Atmosphere, sea-level static (hereinafter ISA SLS) design point pressure ratio of the axi-centrifugal compressor is from 12 to 16, and a ratio of the ISA SLS pressure rise across the axial compression stages to the ISA SLS pressure rise across the centrifugal compression stage is from 0.75 to 1.
-
-
-
-
-
-
-
-
-
Search Results
4669
records
(took 0.037 seconds)
