公开(公告)号：US20230175750A1

公开(公告)日：2023-06-08

申请号：US18057270

申请日：2022-11-21

Applicant: ROLLS-ROYCE plc

Inventor： Chloe J. PALMER ,  Ian M. BUNCE

IPC: F25B49/02 ,  G01N25/12 ,  F25B9/00 ,  F25B9/06

CPC classification number: F25B49/02 ,  G01N25/12 ,  F25B9/008 ,  F25B9/06 ,  F25B2600/2515 ,  F25B2309/061

Abstract: A sensor assembly is shown for sensing a crossing of the critical point in a system utilising a working fluid in a transcritical cycle passing through the critical point. A first broadband acoustic sensor is located upstream of a component and a second broadband acoustic sensor is located downstream of the component, each of which are arranged to detect high-frequency and low-frequency sounds caused by the crossing of the critical point. A flow regulation device regulates flow of working fluid through the component in response to the output of one or both of the first broadband acoustic sensor and the second broadband acoustic sensor, thereby adjusting the location of the crossing of the critical point.

公开(公告)号：US20230166855A1

公开(公告)日：2023-06-01

申请号：US17940046

申请日：2022-09-08

Applicant: ROLLS-ROYCE plc

Inventor： Jamie W. GALLAGHER ,  Daniel BLACKER ,  Hugh J. BLAKEMORE ,  Adrian M. MANSER ,  Jonathan V. WATSON ,  Alexander L. FRY ,  Robert A. BARKER ,  James THORP ,  Marie-Océane PARENT

IPC: B64D27/26 ,  F02C7/20

CPC classification number: B64D27/26 ,  F02C7/20 ,  B64D2027/264 ,  F05D2220/323 ,  F05D2240/90 ,  F05D2260/20

Abstract: A gas turbine engine comprises, in axial flow sequence, a fan assembly, a compressor module, a turbine module, and an exhaust module. The gas turbine engine comprises first and second engine mount planes. The first and second engine mount planes are configured to support gas turbine engine in machine body. The gas turbine engine has axial length L, with axial length extending from inlet face of engine to exhaust face of engine. The first engine mount plane is positioned axially along gas turbine engine at first engine mount plane position, with first engine mount plane position within a range of between 0.24*L to 0.32*L from the inlet face of the engine. The second engine mount plane is positioned axially along gas turbine engine at second engine mount plane position, with second engine mount plane position within a range of between 0.73*L to 0.79*L from the inlet face of the engine.

公开(公告)号：US11661892B2

公开(公告)日：2023-05-30

申请号：US17412638

申请日：2021-08-26

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

Inventor： Stephan Uhkötter ,  Rens Douma ,  Uwe Kracht ,  Mark Binnington

IPC: F16H57/04 ,  F02C7/36 ,  F02K3/06 ,  F02C7/06

CPC classification number: F02C7/36 ,  F02C7/06 ,  F02K3/06 ,  F16H57/043 ,  F16H57/0479 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2240/54 ,  F05D2260/40311 ,  F05D2260/98

Abstract: A planetary gear box for a gas turbine engine, has a planet carrier with a carrier element and a planet gear. The planet gear is mounted rotatably via a plain bearing on the carrier element. An oil feed pocket is provided in the region of an outer side of the carrier element, via which feed pocket oil can be passed into a bearing gap between the outer side of the carrier element and an inner side of the planet gear. In the circumferential region of a main load direction of the plain bearing, the carrier element is formed with at least one channel carrying transmission oil. The channel extends in the carrier element radially inside the outer side of the carrier element, extending in the axial direction of the carrier element, and includes a cross section closed with respect to the bearing gap.

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.