公开(公告)号：US20230324319A1

公开(公告)日：2023-10-12

申请号：US17853184

申请日：2022-06-29

Applicant: ROLLS-ROYCE PLC

Inventor： Craig W. BEMMENT ,  Paul W. FERRA ,  Alastair G. HOBDAY ,  Benjamin J. KEELER ,  Kevin R. MCNALLY ,  Andrea MINELLI ,  Martin K. YATES

IPC: G01N25/22 ,  F02C7/22

CPC classification number: G01N25/22 ,  F02C7/22 ,  F05D2220/323

Abstract: A method of checking refuelling of an aircraft comprising a gas turbine engine and a fuel tank arranged to provide fuel to the gas turbine engine comprises: receiving an input of calorific value data for fuel provided to the aircraft on refuelling; independently determining at least one of: (i) the calorific value of fuel supplied to the gas turbine engine in use; and (ii) the calorific value of the fuel provided to the aircraft on refuelling; and providing an alert if the determined calorific value is inconsistent with the calorific value data input received

公开(公告)号：US20230272753A1

公开(公告)日：2023-08-31

申请号：US18135526

申请日：2023-04-17

Applicant: ROLLS-ROYCE PLC

Inventor： Craig W. BEMMENT

IPC: F02C9/24 ,  F02C9/18 ,  F01D19/00

CPC classification number: F02C9/24 ,  F02C9/18 ,  F01D19/00 ,  F02C7/36

Abstract: A gas turbine engine for an aircraft and a method of operating a gas turbine engine on an aircraft. Embodiments disclosed include a gas turbine engine for an aircraft including: an engine core has a turbine, a compressor, and a core shaft; a fan located upstream of the engine core, the fan has a plurality of fan blades; a nacelle surrounding the engine core and defining a bypass duct and bypass exhaust nozzle; and a gearbox that receives an input from the core shaft and outputs drive to the fan wherein the gas turbine engine is configured such that a jet velocity ratio of a first jet velocity exiting from the bypass exhaust nozzle to a second jet velocity exiting from an exhaust nozzle of the engine core at idle conditions is greater by a factor of 2 or more than the jet velocity ratio at maximum take-off conditions.

公开(公告)号：US20230193832A1

公开(公告)日：2023-06-22

申请号：US18099490

申请日：2023-01-20

Applicant: ROLLS-ROYCE PLC

Inventor： Peter SWANN ,  David M. BEAVEN ,  Craig W. BEMMENT ,  Alastair G. HOBDAY ,  Benjamin J. KEELER ,  Christopher P. MADDEN ,  Martin K. YATES

IPC: F02C9/00 ,  B64D47/00 ,  G01N21/3577 ,  B64D27/10 ,  G01N21/33 ,  G01N33/28 ,  G01N21/64

CPC classification number: F02C9/00 ,  B64D47/00 ,  G01N21/3577 ,  B64D27/10 ,  G01N21/33 ,  G01N33/287 ,  G01N21/64 ,  B64D37/00

Abstract: A method of generating a maintenance schedule for an aircraft including one or more gas turbine engines powered by an aviation fuel. The method includes: determining one or more fuel characteristics of the fuel; and generating a maintenance schedule according to the one or more fuel characteristics. Also disclosed is a method of maintaining an aircraft, a maintenance schedule generation system and an aircraft.

公开(公告)号：US20230193777A1

公开(公告)日：2023-06-22

申请号：US17853405

申请日：2022-06-29

Applicant: ROLLS-ROYCE plc

Inventor： Peter SWANN ,  David M. BEAVEN ,  Craig W. BEMMENT ,  Alastair G. HOBDAY ,  Benjamin J. KEELER ,  Christopher P. MADDEN ,  Martin K. YATES

IPC: F01D21/00 ,  F02C9/28

CPC classification number: F01D21/003 ,  F02C9/28 ,  F05D2220/323 ,  F05D2260/80 ,  F05D2270/0831 ,  F05D2270/708 ,  F05D2270/804

Abstract: The present application discloses a method of determining one or more fuel characteristics of an aviation fuel suitable for powering a gas turbine engine of an aircraft. The method comprises: determining, during use of the gas turbine engine, one or more exhaust content parameters by performing a sensor measurement on an exhaust of the gas turbine engine; and determining one or more fuel characteristics of the fuel based on the one or more exhaust parameters. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.

公开(公告)号：US20190063368A1

公开(公告)日：2019-02-28

申请号：US16106813

申请日：2018-08-21

Applicant: ROLLS-ROYCE plc

Inventor： Benedict R. PHELPS ,  Mark J. WILSON ,  Gabriel GONZALEZ-GUTIERREZ ,  Nigel HS SMITH ,  Marco BARALE ,  Kashmir S. JOHAL ,  Stephane MM BARALON ,  Craig W. BEMMENT

IPC: F02K3/06 ,  F02C3/06 ,  F01D5/14

Abstract: A gas turbine engine 10 is provided in a fan root to tip pressure ratio, defined as the ratio of the mean total pressure of the flow at the fan exit that subsequently flows through the engine core (P102) to the mean total pressure of the flow at the fan exit that subsequently flows through the bypass duct (P104), is no greater than a certain value. The gas turbine engine 10 may provide improved efficiency when compared with conventional engines, whilst retaining an acceptable flutter margin.

公开(公告)号：US20250059922A1

公开(公告)日：2025-02-20

申请号：US18936481

申请日：2024-11-04

Applicant: ROLLS-ROYCE PLC

Inventor： Peter SWANN ,  Craig W. BEMMENT ,  Christopher P. MADDEN

IPC: F02C9/26 ,  B64D27/10 ,  B64D37/30 ,  F02C7/22 ,  F23R3/36

Abstract: A gas turbine engine for an aircraft includes a staged combustion system having pilot fuel injectors and main fuel injectors. The gas turbine engine further includes a fuel delivery regulator arranged to control delivery of fuel to the pilot and main fuel injectors, and a fuel characteristic determination module configured to determine one or more fuel characteristics of the fuel being supplied to the staged combustion system. A controller is configured to determine a staging point defining the point at which the staged combustion system is switched between pilot-only operation and pilot-and-main operation, the staging point being determined based on the determined one or more fuel characteristics, the controller being configured to control the staged combustion system according to the determined staging point.

公开(公告)号：US20240352898A1

公开(公告)日：2024-10-24

申请号：US18755944

申请日：2024-06-27

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 power system for an aircraft comprises a gas turbine engine, arranged to burn a fuel in a combustor so as to provide power to the aircraft; a plurality of fuel tanks arranged to contain fuel to be used to provide power to the aircraft; and a fuel manager. A first fuel tank of the plurality of fuel tanks is arranged to contain a first fuel, and a second tank of the plurality of fuel tanks is arranged to contain a second, different, fuel. The fuel manager is arranged to store information on the fuel contained in each fuel tank and to control fuel supply so as to take fuel from the second tank for engine start-up, before switching to the first fuel tank.

公开(公告)号：US20240263582A1

公开(公告)日：2024-08-08

申请号：US18634305

申请日：2024-04-12

Applicant: Rolls-Royce plc

Inventor： Craig W. BEMMENT ,  Alastair G. Hobday ,  Benjamin J. Keeler ,  Christopher P. Madden ,  Andrea Minelli ,  Andrew T. Smith ,  Peter Swann ,  Martin K. Yates

IPC: F02C7/14 ,  F02C7/224 ,  F02C7/36

CPC classification number: F02C7/14 ,  F02C7/224 ,  F02C7/36 ,  F05D2220/323 ,  F05D2260/213

Abstract: A method of operating a gas turbine engine including an engine core including a turbine, compressor, combustor to combust a fuel, and core shaft connecting the turbine and compressor; a fan upstream of the engine core; a fan shaft; a gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft; a primary oil loop system to supply oil to the gearbox; and a heat exchange system. The method includes controlling the heat exchange system to adjust fuel viscosity to be lower than or equal to 0.58 mm2/s on entry to the combustor at cruise conditions.

公开(公告)号：US20240210035A1

公开(公告)日：2024-06-27

申请号：US18211622

申请日：2023-06-20

Applicant: ROLLS-ROYCE PLC

Inventor： Christopher P. MADDEN ,  Craig W. BEMMENT ,  Andrew T. SMITH ,  Peter SWANN

IPC: F23R3/28 ,  B64D27/10 ,  F02C7/264

CPC classification number: F23R3/28 ,  B64D27/10 ,  F02C7/264 ,  F05D2240/35

Abstract: A method of operating a gas turbine engine; the gas turbine engine includes a combustor. The combustor includes a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber. The plurality of fuel spray nozzles includes a first subset of fuel spray nozzles and a second subset of fuel spray nozzles. The combustor is operable in a condition in which the first subset of fuel spray nozzles are supplied with more fuel than the second subset of fuel spray nozzles. A ratio of the number of fuel spray nozzles in the first subset of fuel spray nozzles to the number of fuel spray nozzles in the second subset of fuel spray nozzles is in the range of 1:2 to 1:5. The method includes: providing fuel to the one or more fuel-oil heat exchangers. Also provided is a gas turbine engine for an aircraft.

公开(公告)号：US20240209799A1

公开(公告)日：2024-06-27

申请号：US18337568

申请日：2023-06-20

Applicant: ROLLS-ROYCE plc

Inventor： Craig W. BEMMENT ,  Alastair G. HOBDAY ,  Benjamin J. KEELER ,  Christopher P. MADDEN ,  Andrea MINELLI ,  Andrew T. SMITH ,  Peter SWANN ,  Martin K. YATES

IPC: F02C9/38 ,  F02C7/14 ,  F02C7/16

CPC classification number: F02C9/38 ,  F02C7/14 ,  F02C7/16 ,  F05D2260/213

Abstract: A method of operating a gas turbine engine including: a combustor arranged to combust a fuel; and a fuel management system arranged to provide the fuel to the combustor, wherein the fuel management system includes two fuel-oil heat exchangers through which oil and fuel flow, which are arranged to transfer heat between the oil and fuel and include primary and secondary fuel-oil heat exchangers; a fuel pump arranged to deliver the fuel to the combustor, wherein the fuel pump is located between the heat exchangers; and a recirculation valve located downstream of the primary heat exchanger, the recirculation valve arranged to allow a controlled amount of fuel which has passed through the primary heat exchanger to be returned to the inlet. The method includes selecting one or more fuels such that the calorific value of the fuel provided to the gas turbine engine is at least 43.5 MJ/kg.