公开(公告)号：US20230159177A1

公开(公告)日：2023-05-25

申请号：US18053015

申请日：2022-11-07

Applicant: ROLLS-ROYCE plc

Inventor： David R. TRAINER ,  Francisco Javier CHIVITE ZABALZA ,  Mark SWEET ,  Luke GEORGE ,  Gian INCERPI

IPC: B64D27/24 ,  H02M3/28 ,  H02J1/10 ,  H02J7/34

CPC classification number: B64D27/24 ,  H02M3/28 ,  H02J1/106 ,  H02J7/34 ,  B64D2221/00 ,  H02J2310/44

Abstract: The disclosure relates to an electrical power system for providing a stabilised DC voltage to a power bus. Example embodiments include an electrical power system comprising: a DC power bus having first and second DC power bus terminals; an electrical storage unit having first and second terminals, the second terminal connected to the second DC power bus terminal; a DC:DC converter having first and second DC:AC converters and a transformer connected between the first and second DC:AC converters, the first DC:AC converter connected between the first terminal of the electrical storage unit and the first DC power bus terminal; and a controller connected to control a switching operation of one or both of the first and second DC:AC converters.

公开(公告)号：US11649767B2

公开(公告)日：2023-05-16

申请号：US17484371

申请日：2021-09-24

Applicant: ROLLS-ROYCE plc

Inventor： Stephen J Bradbrook ,  Martin N Goodhand ,  Paul M Hield ,  Andrew Parsley ,  Natalie C Wong ,  Robert J Corin ,  Thomas S Binnington

IPC: F02C7/18 ,  F02C6/08 ,  F28D9/00 ,  B64D33/02 ,  F28D21/00

CPC classification number: F02C7/185 ,  F02C6/08 ,  F28D9/0018 ,  B64D2033/0286 ,  F05D2260/20 ,  F28D2021/0021

Abstract: A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, and an exhaust module. The fan assembly includes a plurality of fan blades defining a fan diameter (D). The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and the heat exchanger module includes a plurality of radially-extending hollow vanes arranged in a circumferential array with a channel extending axially between each pair of adjacent hollow vanes. An airflow entering the heat exchanger module is divided between a set of vane airflows through each of the hollow vanes and a set of channel airflows through each of the channels.

公开(公告)号：US11649764B2

公开(公告)日：2023-05-16

申请号：US17484622

申请日：2021-09-24

Applicant: ROLLS-ROYCE plc

Inventor： Natalie C Wong ,  Thomas S Binnington ,  David A Jones ,  Daniel Blacker

IPC: F02C7/04 ,  F02C7/18 ,  B64D27/10 ,  B64D33/02 ,  B64D33/04 ,  B64D33/08 ,  B64D27/20 ,  B64D33/10 ,  F02K3/06 ,  F02K3/075 ,  F02C7/08 ,  F02C7/12 ,  F02C7/14 ,  F01D9/06 ,  F02K3/115

CPC classification number: F02C7/04 ,  B64D27/10 ,  B64D27/20 ,  B64D33/02 ,  B64D33/04 ,  B64D33/08 ,  B64D33/10 ,  F01D9/065 ,  F02C7/08 ,  F02C7/12 ,  F02C7/14 ,  F02C7/18 ,  F02K3/06 ,  F02K3/075 ,  B64D2033/024 ,  B64D2033/0286 ,  F02K3/115 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2260/213

Abstract: An aircraft comprises a machine body. The machine body encloses a turbofan gas turbine engine and a plurality of ancillary systems. The turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a combustor module, a turbine module, and an exhaust module. The machine body comprises a single fluid inlet aperture, with the fluid inlet aperture being configured to allow a fluid cooling flow to enter the machine body and to pass through the heat exchanger module. The heat exchanger module is configured to transfer a waste heat load from the gas turbine engine and the ancillary systems to the fluid cooling flow prior to an entry of the entire fluid cooling flow into the fan module.

公开(公告)号：US11643980B1

公开(公告)日：2023-05-09

申请号：US17853233

申请日：2022-06-29

Applicant: ROLLS-ROYCE plc

Inventor： Craig W Bemment ,  Benjamin J Keeler ,  Paul W Ferra ,  Alastair G Hobday ,  Kevin R McNally ,  Andrea Minelli ,  Martin K Yates

IPC: F02C9/28

CPC classification number: F02C9/28 ,  F05D2220/323 ,  F05D2270/30

Abstract: A method of determining a calorific value of fuel supplied to a gas turbine engine of an aircraft comprises sensing at least one engine parameter during a first time period of aircraft operation during which the gas turbine engine uses the fuel; and, based on the at least one sensed engine parameter, determining a calorific value of the fuel. The sensing may be repeated such that the at least one engine parameter is monitored over time. The gas turbine engine may be a propulsive gas turbine engine of the aircraft or a gas turbine engine of an auxiliary power unit of the aircraft.

公开(公告)号：US11643978B2

公开(公告)日：2023-05-09

申请号：US17570433

申请日：2022-01-07

Applicant: ROLLS-ROYCE plc

Inventor： Peter Swann ,  Christopher P Madden

IPC: F02C9/28 ,  F23R3/34 ,  F02C7/22

CPC classification number: F02C9/28 ,  F23R3/343 ,  F02C7/22 ,  F05D2220/323 ,  F05D2270/07 ,  F05D2270/13 ,  F05D2270/303 ,  F05D2270/311 ,  F05D2270/313 ,  F05D2270/335

Abstract: An aircraft including lean-burn gas turbine engines operating in pilot-plus-mains mode with a given initial fuel flow W0, a method of controlling the optical depth of contrails produced by a first group of engines includes the steps of (i) reducing fuel flow to each engine in the first group to change the operation of each engine from pilot-plus-mains mode to pilot-only mode, and (ii) adjusting fuel flow to one or more engines in a second group of engines such that the total fuel flow to engines of the second group is increased, all engines of the second group remaining in pilot-plus-mains mode, and wherein the set of lean-burn engines consists of the first and second groups. Depending on atmospheric conditions, the average optical depth of contrails produced by the engines may be enhanced or reduced compared to when all engines operate in pilot-plus-mains mode with a fuel flow W0.

公开(公告)号：US11643217B2

公开(公告)日：2023-05-09

申请号：US17320299

申请日：2021-05-14

Applicant: ROLLS-ROYCE plc

Inventor： Matthew S. Cartwright

IPC: B64D27/24 ,  B64D27/10 ,  B60L50/60 ,  H02J4/00

CPC classification number: B64D27/24 ,  B60L50/60 ,  B64D27/10 ,  H02J4/00 ,  B60L2200/10 ,  B64D2221/00

Abstract: A method of operating an aircraft electrical power distribution system comprises determining a measure of ambient pressure; and setting a target operating voltage in accordance with the measure of ambient pressure. The method further comprises controlling the operating voltage in accordance with the set target operating voltage. The target operating voltage may refer to a distribution voltage of the aircraft. An aircraft electrical power distribution system is also disclosed, comprising: a sensor configured to determine a measure of ambient pressure; a controller configured to set a target operating voltage in accordance with the measure of ambient pressure, and a voltage regulator configured to regulate the operating voltage in accordance with the set target value.

公开(公告)号：US20230136376A1

公开(公告)日：2023-05-04

申请号：US17957778

申请日：2022-09-30

Applicant: Rolls-Royce plc

Inventor： David R. TRAINER ,  Francisco Javier CHIVITE ZABALZA ,  Mark SWEET ,  Gian INCERPI ,  Luke GEORGE

IPC: H02J7/00 ,  H02M3/335 ,  B64D27/24

Abstract: An electrical power system including: an electrical power source, a power electronics converter, an electrical network, a current limiting diode and a controllable circuit interruption device, wherein: the current limiting diode is configured to limit a fault current passing between the electrical power source and the electrical network in a fault condition; and the controllable circuit interruption device is configured to interrupt the fault current in response to a determination that the electrical power system is in the fault condition.

公开(公告)号：US20230134139A1

公开(公告)日：2023-05-04

申请号：US18050825

申请日：2022-10-28

Applicant: ROLLS-ROYCE plc

Inventor： Damian MARTIN ,  James E. CLISSOLD

IPC: F23R3/28 ,  F02C7/28

Abstract: A combustor arrangement includes a fuel injector, and a seal arranged around the fuel injector and having an upstream end and a downstream end. The seal includes an annular body at least partially abutting the fuel injector. The annular body includes an inner surface facing the fuel injector and an outer surface radially spaced apart from the inner surface relative to the central axis. The annular body further includes a plurality of slots disposed on the inner surface and circumferentially spaced apart from each other relative to the central axis. Each slot axially extends at least partially from the downstream end to the upstream end. Each slot is disposed in fluid contact with the fuel injector. The seal also includes a flange radially extending from the outer surface of the annular body at the upstream end.

公开(公告)号：US20230132101A1

公开(公告)日：2023-04-27

申请号：US18045857

申请日：2022-10-12

Applicant: ROLLS-ROYCE plc

Inventor： Christopher A MURRAY

IPC: B64D13/06 ,  F02C7/36 ,  F02C7/32

Abstract: A cabin blower system, for an aircraft, comprising: a cabin blower compressor, for compressing air for delivery to a cabin of an aircraft, comprising a compressor drive shaft running on a contactless bearing system; and a transmission comprising an input and an output, the input being arranged to receive power from an engine of the aircraft and the output being arranged to mechanically drive the cabin blower compressor, wherein the output of the transmission is mechanically coupled with the compressor drive shaft via a flexible drive coupling.

公开(公告)号：US20230125918A1

公开(公告)日：2023-04-27

申请号：US17973609

申请日：2022-10-26

Applicant: Rolls-Royce Deutschland Ltd & Co KG ,  Rolls-Royce plc

Inventor： Matthew THOMSON ,  Romek OTT ,  Igor SIKORSKI ,  Sabina HEYEN

IPC: F02C7/18 ,  F23R3/04 ,  F23R3/16 ,  F23R3/42

Abstract: A combustion chamber assembly includes a through hole on the combustion chamber wall bounded on an outer side of the wall by a hole edge and a combustion chamber shingle having a collar bounding a mixing air hole on the outer side of the wall and protruding with a first collar portion beyond the hole edge on the outer side of the wall. A cooling air opening is formed on an inner circumferential surface of a duct portion of the mixing air hole adjoining the first collar portion and extending in the direction of a combustion space, the cooling air opening leading into a cooling air duct which extends through the duct portion and via which cooling air is guided out of the mixing air hole in a direction of a hot side of the shingle facing the combustion space.