公开(公告)号：US20230193838A1

公开(公告)日：2023-06-22

申请号：US18084083

申请日：2022-12-19

Applicant: ROLLS-ROYCE plc

Inventor： Peter SWANN ,  Craig W. BEMMENT ,  Alastair G. HOBDAY ,  Benjamin J. KEELER ,  Christopher P. MADDEN

IPC: F02C9/40 ,  F01D21/00 ,  F02C9/28

CPC classification number: F02C9/40 ,  F01D21/003 ,  F02C9/28 ,  F05D2220/323 ,  F05D2260/83 ,  F05D2270/07 ,  F05D2270/71

Abstract: A method of operating an aircraft that includes a propulsion system. The propulsion system includes a gas turbine engine and a fuel tank arranged to provide fuel to the gas turbine engine. The method includes: determining at least one fuel characteristic of the fuel arranged to be provided to the gas turbine engine; and controlling the propulsion system based on the at least one fuel characteristic.

公开(公告)号：US20230193773A1

公开(公告)日：2023-06-22

申请号：US17560233

申请日：2021-12-22

Applicant: Rolls-Royce plc

Inventor： Daniel Clark ,  Michael J. Whittle ,  Carl Boettcher ,  David C. Wright

IPC: F01D9/06 ,  F01D5/28

CPC classification number: F01D9/065 ,  F01D5/282 ,  F01D5/284 ,  F05D2240/12 ,  F05D2300/6033

Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a plurality of turbine vanes, an outer vane support, and an inner vane support. The plurality of turbine vanes comprise ceramic matrix composite material and are adapted to interact with hot gases flowing through a gas path of the gas turbine engine during use of the turbine vane assembly. A spar system couples the inner vane support with the outer vane support.

公开(公告)号：US20230192979A1

公开(公告)日：2023-06-22

申请号：US18058912

申请日：2022-11-28

Applicant: ROLLS-ROYCE plc

Inventor： Eduardo SANTANA DE VEGA ,  Giuliano ALLEGRI ,  Stephen HALLETT ,  Ian HAMERTON ,  Bing ZHANG

IPC: C08J5/24 ,  B29C70/82

CPC classification number: C08J5/246 ,  B29C70/82 ,  C08J2363/00 ,  C08J2375/00 ,  C08J2379/08 ,  C08J2367/00 ,  C08J2479/06

Abstract: A Z-pin for increasing a delamination resistance of continuous fibre-reinforced polymer composites, formed of a composite material including a polymer matrix, and a plurality of fibres embedded in the polymer matrix and aligned along the length direction of Z-pin, the fibres having an elongation at break of at least 2% and a tensile strength of at least 5 GPa, the polymer matrix having an elongation at break equal to or greater than the elongation at break of the fibres, and a tensile strength of at least 120 MPa.

公开(公告)号：US20230191610A1

公开(公告)日：2023-06-22

申请号：US18075877

申请日：2022-12-06

Applicant: ROLLS-ROYCE plc

Inventor： Andrew D. NORTON ,  Matteo RUSSO ,  Abdelkhalick MOHAMMAD

IPC: B25J9/16 ,  B25J9/06 ,  B25J19/06

CPC classification number: B25J9/1682 ,  B25J9/06 ,  B25J9/1633 ,  B25J9/163 ,  B25J19/066

Abstract: A control system for a compliant robotic system including at least two compliant robots having actuator packs, the control system including: an individual local control system associated with each actuator pack, the local control system providing control signals to the actuator causing movement within the robots, an overall control system controlling the overall motion of robots when proximate within a workspace, the overall control signal providing signals to the actuators associated with the robots, so as to cause linked movement of the continuum arm robots, and wherein each individual control system is provided with a clock synchronized with the other, and wherein the overall control system is provided with a redundancy control system that limits the motion of the compliant robots within certain degrees of freedom, so that the motion of the at least two complaint robots does not conflict when operating under the overall control system.

公开(公告)号：US11680529B2

公开(公告)日：2023-06-20

申请号：US17108452

申请日：2020-12-01

Applicant: ROLLS-ROYCE plc

Inventor： Graham P Bruce

IPC: F02C7/36 ,  H02J3/36 ,  H02K7/18 ,  B64D27/10 ,  B64D27/24 ,  B64D27/02

CPC classification number: F02C7/36 ,  H02J3/36 ,  H02K7/1823 ,  B64D27/10 ,  B64D27/24 ,  B64D2027/026

Abstract: An electrical system for connecting a rotary electric machine to dc networks operating at different voltages, the electric machine having polyphase winding sets each having a respective index. The electrical system has a first set of ac-dc converter circuits connected in a modular multilevel configuration, each ac-dc converter circuit having a respective index and an ac interface for connection with a corresponding winding set, and in which the modular multilevel configuration has dc outputs each having a respective index. The electrical system also has a set of dc-dc converter circuits each having a respective index and being configured to convert dc power between a voltage at a first dc interface and a voltage at a second dc interface, where a first dc interface of the nth dc-dc converter circuit is connected with the dc outputs of the modular multilevel configuration.

公开(公告)号：US20230184171A1

公开(公告)日：2023-06-15

申请号：US17988504

申请日：2022-11-16

Applicant: ROLLS-ROYCE plc

Inventor： Gareth E. MOORE ,  Paul R. DAVIES ,  Stephen M. HUSBAND ,  David R. TRAINER ,  David P. SCOTHERN ,  Luke GEORGE ,  Douglas M M. HERBERT

IPC: F02C7/262

CPC classification number: F02C7/262 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2260/85 ,  F05D2270/092 ,  F05D2270/093

Abstract: Multi-engine aircraft power and propulsion systems and methods of restarting an engine of a multi-engine aircraft during fight are provided. One such method comprises: determining a condition to the effect that a flame in the combustion equipment of the second gas turbine engine has been extinguished; responsive to the determination, supplying electrical power from the electrical energy storage system to one or more of the electric machines of the second gas turbine engine and operating said one or more electric machines as motors to limit a reduction in a speed of the one or more spools of the second gas turbine engine following extinguishment of the flame in its combustion equipment; and restarting the second gas turbine engine by relighting the combustion equipment of the second gas turbine engine.

公开(公告)号：US20230184165A1

公开(公告)日：2023-06-15

申请号：US18062721

申请日：2022-12-07

Applicant: ROLLS-ROYCE plc

Inventor： Robert W. HICKS ,  Nicholas E. CHILTON

IPC: F02C7/047 ,  F01D25/02

CPC classification number: F02C7/047 ,  F01D25/02

Abstract: A vane assembly for a gas turbine engine which is a single unitary component that includes an aerofoil. A leading edge passageway is disposed proximal to a leading edge of the aerofoil and configured to receive a flow of a fluid therein. The vane assembly further includes a connecting passageway fluidly communicating the leading edge passageway with a trailing edge distribution passageway that is spaced apart from the leading edge, the leading edge passageway and a trailing edge of the aerofoil. The vane assembly further includes a plurality of trailing edge passageways disposed proximal to a pressure surface of the aerofoil and extending from the trailing edge distribution passageway towards the trailing edge along a chordwise direction. Each trailing edge passageway is configured to discharge the fluid through a corresponding passageway outlet disposed on the pressure surface and in fluid communication with a corresponding trailing edge passageway.

公开(公告)号：US20230184128A1

公开(公告)日：2023-06-15

申请号：US17940614

申请日：2022-09-08

Applicant: ROLLS-ROYCE plc

Inventor： Paul R. DAVIES ,  Gareth E. MOORE ,  Stephen M. HUSBAND ,  David R. TRAINER ,  David P. SCOTHERN ,  Luke GEORGE

IPC: F01D15/10 ,  F02K3/06

CPC classification number: F01D15/10 ,  F02K3/06 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2260/232 ,  F05D2260/42 ,  F05D2200/13 ,  F05D2200/14

Abstract: A gas turbine engine for an aircraft comprises, in axial flow sequence, a compressor module, a combustor module, and a turbine module. The gas turbine engine further comprises a first electric machine that is rotationally connected to the turbine module, and an electrical energy storage unit. The gas turbine engine is configured to generate a maximum dry thrust T (N). The first electric machine is configured to generate a maximum electrical power PEM1 (W). The electrical energy storage unit has an energy storage capacity E (Wh), a maximum charge rate C (h−1), and a maximum discharge rate D (h−1). The electrical energy storage unit is configured to store electrical energy that may be generated by the first electric machine.

公开(公告)号：US20230182918A1

公开(公告)日：2023-06-15

申请号：US17988538

申请日：2022-11-16

Applicant: ROLLS-ROYCE plc

Inventor： Gareth E MOORE ,  Paul R DAVIES ,  Stephen M HUSBAND ,  David R TRAINER ,  David P SCOTHERN ,  Luke GEORGE ,  Douglas M M HERBERT

IPC: B64D31/06 ,  B64D27/24 ,  F01D15/10 ,  B64D27/10

CPC classification number: B64D31/06 ,  B64D27/24 ,  F01D15/10 ,  B64D27/10 ,  B64D2027/026

Abstract: Aircraft power and propulsion systems and methods of operating the systems, one method includes: operating electric machines of gas turbine engines as generators to extract mechanical power from spools and generating electrical power therefrom; meeting an electrical power demand of a plurality of electrical loads connected with an electrical system by supplying the plurality of electrical loads with electrical power generated by the electric machines; determining when there is an electrical system and/or the gas turbine engine fault and an amount of electrical power generated by the power and propulsion system is reduced to a lower level; and responsive to the determination: during a time period ΔT, controlling the plurality of electrical loads reducing the electrical power demand; and during the time period ΔT, meeting at least part of the electrical power demand of the plurality of electrical loads by discharging the electrical energy storage system.

公开(公告)号：US20230182911A1

公开(公告)日：2023-06-15

申请号：US18061330

申请日：2022-12-02

Applicant: ROLLS-ROYCE plc

Inventor： Richard G STRETTON

IPC: B64D27/26 ,  B64D27/10 ,  B64D33/08 ,  F02C7/20

CPC classification number: B64D27/26 ,  B64D27/10 ,  B64D33/08 ,  F02C7/20 ,  B64D2027/268 ,  F05D2220/323 ,  F05D2240/90

Abstract: A gas turbine engine includes a support structure for attaching the engine to an aircraft pylon. The support structure includes: an engine-side interface member, a pylon-side interface member interfacing to the engine-side interface member, and a top V-shaped connection formation above the engine core and pair of side V-shaped connection formations on opposite lateral sides of the engine core, each V-shaped connection formation being formed by a pair of connection members meeting at a vertex, the vertex of the top V-shaped connection formation joining to the top of the engine-side interface member, the vertices of the side V-shaped connection formations respectively joining to the bottom ends of the engine-side interface member, and the connection members extending forwardly from their respective vertices to join to front fixation points at the core casing.