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.

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：US20240210039A1

公开(公告)日：2024-06-27

申请号：US18337477

申请日：2023-06-20

Applicant: ROLLS-ROYCE PLC

Inventor： Christopher P MADDEN ,  David M BEAVEN ,  Craig W BEMMENT ,  Paul W FERRA ,  Barani P GUNASEKARAN ,  Benjamin J KEELER ,  Peter SWANN ,  Martin K YATES

IPC: F23R3/34 ,  F02C7/22 ,  F23K5/08

CPC classification number: F23R3/346 ,  F02C7/22 ,  F23K5/08 ,  F05D2240/35 ,  F23K2300/204

Abstract: There is provided a method of operating a gas turbine engine. The gas turbine engine comprises a staged combustor having an arrangement of fuel spray nozzles in which fuel flow is biased to a subset of the nozzles adjacent one or more ignitors during a re-light procedure. The method comprises transferring heat from the oil to the fuel before the fuel enters the combustor so as to lower the fuel viscosity to 0.58 mm2/s or lower on entry to the combustor at cruise conditions. Also disclosed is a gas turbine engine.

公开(公告)号：US20240210038A1

公开(公告)日：2024-06-27

申请号：US18211793

申请日：2023-06-20

Applicant: ROLLS-ROYCE PLC

Inventor： Christopher P MADDEN ,  Craig W BEMMENT ,  Paul W FERRA ,  Benjamin J KEELER ,  Andrea MINELLI ,  Peter SWANN ,  Martin K YATES

IPC: F23R3/34 ,  F02C7/224 ,  F23K5/08

CPC classification number: F23R3/346 ,  F02C7/224 ,  F23K5/08 ,  F23K2300/204

Abstract: A method of operating a gas turbine engine having a lean burn staged combustion system having a combustor in which fuel is combusted. The gas turbine engine includes a fuel-oil heat exchanger arranged to transfer heat between oil and fuel that is provided to the combustor. The method includes transferring heat from the oil to the fuel before the fuel enters the combustor so as to lower the fuel viscosity to 0.58 mm2/s or lower on entry to the combustor at cruise conditions.