公开(公告)号：US20240401531A1

公开(公告)日：2024-12-05

申请号：US18420204

申请日：2024-01-23

Applicant: ROLLS-ROYCE plc

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

IPC: F02C7/14 ,  F02C7/16 ,  F02C7/22

Abstract: A method of operating a gas turbine engine and a gas turbine engine includes a fuel delivery system arranged to provide fuel, a combustor arranged to combust at least a proportion of the fuel, a primary fuel-oil heat exchanger arranged to have up to 100% of the fuel provided by the fuel delivery system flow therethrough, and a secondary fuel-oil heat exchanger arranged to have a proportion of the fuel from the primary fuel-oil heat exchanger flow therethrough. Fuel is arranged to flow from the primary fuel-oil heat exchanger to the secondary fuel-oil heat exchanger whereas oil is arranged to flow from the secondary fuel-oil heat exchanger to the primary fuel-oil heat exchanger. A fuel viscosity is adjusted to a maximum of 0.58 mm2/s on entry to the combustor at cruise conditions.

公开(公告)号：US20230323821A1

公开(公告)日：2023-10-12

申请号：US18125431

申请日：2023-03-23

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 refuelling an aircraft comprising a gas turbine engine and a fuel tank arranged to provide fuel to the gas turbine engine comprises obtaining an amount of energy required for an intended flight profile; obtaining a calorific value of fuel available to the aircraft for refuelling; calculating the amount of the available fuel needed to provide the required energy; and refuelling the aircraft with the calculated amount of the available fuel. The calculating the amount of the available fuel needed to provide the required energy may comprise obtaining an energy content of fuel already in the fuel tank and subtracting that from the determined amount of energy required for the intended flight profile.

公开(公告)号：US20230193837A1

公开(公告)日：2023-06-22

申请号：US17853333

申请日：2022-06-29

Applicant: ROLLS-ROYCE PLC

Inventor： Benjamin J KEELER ,  David M BEAVEN ,  Craig W BEMMENT ,  Paul W FERRA ,  Kevin R MCNALLY ,  Andrea MINELLI ,  Martin K YATES

IPC: F02C9/28

CPC classification number: F02C9/28 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2270/303 ,  F05D2270/309 ,  F05D2270/3013

Abstract: A gas turbine engine includes: a combustor that combust the fuel and having an exit, a combustor exit temperature (T40) is the average temperature of flow and a combustor exit pressure (P40) is the total pressure there; a turbine including a rotor having a leading edge and a trailing edge, and wherein a turbine rotor entry temperature (T41) is an average temperature of flow at the leading edge and a turbine rotor entry pressure (P41) is the total pressure there; and a compressor having an exit, wherein a compressor exit temperature (T30) is the average temperature of flow at the exit from the compressor and a compressor exit pressure (P30) is the total pressure there (all at cruise conditions). A method of determining at least one fuel characteristic includes changing a fuel supplied to the engine; and determining a change in a relationship between T30 or P30, T40 and T41, or of P40 and P41, respectively.

公开(公告)号：US20240209789A1

公开(公告)日：2024-06-27

申请号：US18337717

申请日：2023-06-20

Applicant: ROLLS-ROYCE plc

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

IPC: F02C7/224 ,  F02C7/06 ,  F02C7/32

CPC classification number: F02C7/224 ,  F02C7/06 ,  F02C7/32 ,  F05D2260/221 ,  F05D2260/98

Abstract: A method of operating a gas turbine engine having an engine core having a turbine, a compressor, a combustor to combust a fuel, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core; a fan shaft; a main gearbox receiving an input from the core shaft and outputting 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 arranged 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 200 to 600 KJ/m3 of heat from the oil to the fuel, using the heat exchange system, at cruise conditions, which may facilitate control of the oil temperature on entry to the main gearbox.

公开(公告)号：US20240209786A1

公开(公告)日：2024-06-27

申请号：US18337603

申请日：2023-06-20

Applicant: ROLLS-ROYCE PLC

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

IPC: F02C7/224 ,  F23R3/28

CPC classification number: F02C7/224 ,  F23R3/28 ,  F05D2260/20

Abstract: A method of operating a gas turbine engine is disclosed, the gas turbine engine comprising a fuel delivery system arranged to provide fuel; a combustor arranged to combust at least a proportion of the fuel; a primary fuel-oil heat exchanger arranged to have up to 100% of the fuel provided by the fuel delivery system flow therethrough; and a secondary fuel-oil heat exchanger arranged to have a proportion of the fuel from the primary fuel-oil heat exchanger flow therethrough. Fuel is arranged to flow from the primary fuel-oil heat exchanger to the secondary fuel-oil heat exchanger and oil is arranged to flow from the secondary fuel-oil heat exchanger to the primary fuel-oil heat exchanger. The method comprises transferring 200-600 KJ/m3 of heat to the fuel from the oil in the primary fuel-oil heat exchanger at cruise conditions.

公开(公告)号：US20240117771A1

公开(公告)日：2024-04-11

申请号：US18212290

申请日：2023-06-21

Applicant: ROLLS-ROYCE PLC

Inventor： Benjamin J KEELER ,  David M BEAVEN ,  Craig W BEMMENT ,  Paul W FERRA ,  Kevin R MCNALLY ,  Andrea MINELLI ,  Martin K YATES

IPC: F02C9/28

CPC classification number: F02C9/28 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2270/3013 ,  F05D2270/303 ,  F05D2270/309

Abstract: A method of determining at least one fuel characteristic of a fuel provided to a gas turbine engine of an aircraft includes making an operational change, the operational change being effected by a controllable component of a propulsion system of which the gas turbine engine forms a part, and being arranged to affect operation of the gas turbine engine, sensing a response to the operational change; and determining the at least one fuel characteristic based on the response to the operational change.

公开(公告)号：US20230323822A1

公开(公告)日：2023-10-12

申请号：US18125477

申请日：2023-03-23

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 ,  F05D2240/35 ,  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 gas turbine engine having a combustor supplied with fuel from a fuel system, the method comprising: determining a mass of the fuel being supplied to the combustor; determining a corresponding volume of the fuel being supplied to the combustor; and determining one or more fuel characteristics based on the determined mass and volume. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.