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：US20210222632A1

公开(公告)日：2021-07-22

申请号：US17143629

申请日：2021-01-07

Applicant: ROLLS-ROYCE PLC

Inventor： Craig W. BEMMENT ,  Pascal DUNNING

IPC: F02C9/00 ,  F02C3/04 ,  F02C7/36 ,  B64D27/10 ,  B64D31/00

Abstract: A gas turbine engine comprises a fan, a compressor, a low pressure turbine and a high pressure turbine. The fan diameter is greater than 250 cm and less than 381 cm; and the gas turbine engine has a first thrust at sea level static conditions and a second thrust at end of runway conditions; and a thrust take-off ratio greater than 1.32; wherein the thrust take-off ratio is the ratio of the first thrust to the second thrust.

公开(公告)号：US20200011238A1

公开(公告)日：2020-01-09

申请号：US16411347

申请日：2019-05-14

Applicant: ROLLS-ROYCE plc

Inventor： Michael O. HALES ,  Craig W. BEMMENT ,  Stephane M. M. BARALON ,  Benjamin J. SELLERS ,  Christopher BENSON ,  Benedict R. PHELPS ,  Mark J. WILSON

IPC: F02C3/073 ,  F02C7/36

Abstract: A gas turbine engine has a cycle operability parameter β in a defined range to achieve improved overall performance, taking into account fan operability and/or bird strike requirements as well as engine efficiency. The defined range of cycle operability parameter β may be particularly beneficial for gas turbine engines in which the fan is driven by a turbine through a gearbox.

公开(公告)号：US20250059923A1

公开(公告)日：2025-02-20

申请号：US18933409

申请日：2024-10-31

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 ,  B64D27/12 ,  B64D37/00 ,  B64D41/00

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 comprising: determining a mass of a fuel being loaded, or which has been loaded, onto the aircraft; determining a corresponding volume of the fuel; determining one or more fuel characteristics of the fuel based on the determined mass and volume. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.

公开(公告)号：US20240209800A1

公开(公告)日：2024-06-27

申请号：US18337531

申请日：2023-06-20

Applicant: ROLLS-ROYCE plc

Inventor： Christopher P. MADDEN ,  David M. BEAVEN ,  Craig W. BEMMENT ,  Paul W. FERRA ,  Benjamin J. KEELER ,  Peter SWANN

IPC: B64D37/34 ,  F02C7/14 ,  F02C7/16 ,  F02C7/232 ,  F02C9/28

CPC classification number: B64D37/34 ,  F02C7/14 ,  F02C7/16 ,  F02C7/232 ,  F02C9/28

Abstract: Provided is a method of operating a gas turbine engine. The engine includes a combustor having a plurality of fuel spray nozzles and a fuel system arranged to provide fuel to the combustor. The system includes: fuel pump; fuel distributing valve downstream of the pump arranged to distribute fuel to the plurality of nozzles and bias fuel flow to the nozzles such that a first subset of the plurality of nozzles receives more fuel than a second subset of the plurality of nozzles; and fuel-oil heat exchanger. The method includes providing a fuel to the combustor and transferring heat from oil to the fuel in the fuel-oil heat exchanger before the fuel enters the combustor so as to lower a viscosity of the fuel to 0.58 mm2/s or lower on entry to the combustor at cruise conditions. Also provided is a gas turbine engine for an aircraft.

公开(公告)号：US20240209780A1

公开(公告)日：2024-06-27

申请号：US18337546

申请日：2023-06-20

Applicant: ROLLS-ROYCE PLC

Inventor： Craig W. BEMMENT ,  Benjamin J. KEELER ,  Kevin R. MCNALLY ,  Andrea MINELLI

IPC: F02C7/14 ,  F02C7/36 ,  F23K5/20

CPC classification number: F02C7/14 ,  F02C7/36 ,  F23K5/20 ,  F05D2260/20 ,  F23K2300/204

Abstract: A method of operating a gas turbine engine, the engine including an engine core with a turbine, a compressor, a combustor arranged to combust a fuel, and a core shaft connecting the turbine to the compressor; a fan upstream of the engine core; a fan shaft; a main 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 lubricate the main gearbox; and a heat exchange system to transfer heat between the oil and the fuel, the oil having an average temperature of at least 180° C. on entry to the heat exchange system at cruise conditions. The method includes transferring heat from the oil to the fuel to lower the fuel viscosity to a value of less than or equal to 0.58 mm2/s on entry to the combustor at cruise conditions.

公开(公告)号：US20230366357A1

公开(公告)日：2023-11-16

申请号：US18225427

申请日：2023-07-24

Applicant: ROLLS-ROYCE plc

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

IPC: F02C9/40 ,  F02C9/28

CPC classification number: F02C9/40 ,  F02C9/28 ,  F05D2270/08 ,  F05D2270/71 ,  F05D2270/31 ,  F05D2220/323 ,  F05D2270/306

Abstract: An aircraft has first and second fuel sources containing fuels with different characteristics, and one or more gas turbine engines powered by the fuels and each having a staged combustion system having pilot and main fuel injectors and being operable in pilot-only and pilot-and-main ranges of operation. The gas turbine engines each have a fuel delivery regulator arranged to control fuel delivery to the pilot and main fuel injectors. The method includes: obtaining a proposed mission description; obtaining nvPM impact parameters for the gas turbine engines, the impact parameters being associated with each operating condition of the proposed mission; calculating an optimised set of one or more fuel characteristics for each flight condition of the proposed flight defined in the flight description based on the nvPM impact parameters; and determining a fuel allocation based on the optimised set of one or more fuel characteristics.

公开(公告)号：US20230313701A1

公开(公告)日：2023-10-05

申请号：US18328225

申请日：2023-06-02

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 ,  F05D2270/804 ,  F05D2270/0831 ,  F05D2270/708 ,  F05D2260/80

Abstract: A method of determining one or more fuel characteristic of an aviation fuel suitable for powering a gas turbine engine of an aircraft is disclosed. The method includes: determining, during use of the gas turbine engine, one or more contrail parameters related to contrail formation by the gas turbine engine. The determining of the one or more contrail parameters includes performing a sensor measurement on a region behind the gas turbine engine in which a contrail is or can be formed. The method also includes determining one or more fuel characteristics of the fuel based on the one or more contrail parameters. A fuel characteristic determination system, a method of operating an aircraft and an aircraft are also disclosed.

公开(公告)号：US20230258101A1

公开(公告)日：2023-08-17

申请号：US18138333

申请日：2023-04-24

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 ,  F05D2270/0831 ,  F05D2270/804 ,  F05D2260/80 ,  F05D2220/323 ,  F05D2270/708

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 including the nvPM content of the exhaust. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.

公开(公告)号：US20230192303A1

公开(公告)日：2023-06-22

申请号：US17853332

申请日：2022-06-29

Applicant: ROLLS-ROYCE plc

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

IPC: B64D27/10 ,  B64D37/04 ,  B64D41/00 ,  F02C7/22 ,  F02C9/26

CPC classification number: B64D27/10 ,  B64D37/04 ,  B64D41/00 ,  F02C7/22 ,  F02C9/26

Abstract: A propulsion system for an aircraft comprises a gas turbine engine; a plurality of fuel tanks arranged to contain different fuels to be used to power the gas turbine engine, wherein the fuels have different calorific values; and a fuel manager. The fuel manager is arranged to store information on the fuel contained in each fuel tank and to control fuel input to the gas turbine engine in operation by selection of a specific fuel or fuel combination from one or more of the plurality of fuel tanks based on thrust demand of the gas turbine engine such that a fuel with a lower calorific value is supplied to the gas turbine engine at lower thrust demand.