公开(公告)号：US20240209787A1

公开(公告)日：2024-06-27

申请号：US18337636

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: F02C7/224 ,  F02C9/28 ,  F23R3/28

CPC classification number: F02C7/224 ,  F02C9/28 ,  F23R3/28 ,  F05D2260/221

Abstract: A method of operating a gas turbine engine is disclosed, the gas turbine engine comprising a combustor arranged to combust a fuel; and a fuel management system arranged to provide the fuel to the combustor. The fuel management system comprises two fuel-oil heat exchangers through which oil and the fuel flow, the heat exchangers arranged to transfer heat to the fuel and comprising a primary fuel-oil heat exchanger and a secondary fuel-oil heat exchanger; and a fuel pump arranged to deliver the fuel to the combustor, wherein the fuel pump is located between the two heat exchangers. The method comprises controlling the fuel management system so as to transfer between 200 and 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：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：US20230322395A1

公开(公告)日：2023-10-12

申请号：US18209136

申请日：2023-06-13

Applicant: ROLLS-ROYCE plc

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

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

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

Abstract: A power system for an aircraft includes one or more gas turbine engines arranged to burn a fuel so as to provide power to the aircraft; a plurality of fuel tanks each arranged to contain a fuel to be used to provide power to the aircraft; and a fuel manager. At least two of the fuel tanks contain different fuels, which have different proportions of a sustainable aviation 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 select a specific fuel accordingly to power at least the majority of operations on the ground. The fuel manager may additionally identify which tank contains the fuel with the highest proportion of a sustainable aviation fuel; and that fuel may be used to power at least the majority of operations on the ground.

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：US20230193836A1

公开(公告)日：2023-06-22

申请号：US17853103

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: F02C9/28

CPC classification number: F02C9/28 ,  F05D2260/80 ,  F05D2270/303 ,  F05D2270/304 ,  F05D2270/708

Abstract: The present application discloses a method of determining one or more fuel characteristics of an aviation fuel used for powering a gas turbine engine of an aircraft. The method comprises: determining one or more performance parameters of the gas turbine engine during a first time period of operation of the gas turbine engine; and determining one or more fuel characteristics of the fuel based on the one or more performance parameters. A method of operating an aircraft, a fuel characteristic determination system, and an aircraft are also disclosed.

公开(公告)号：US20180066582A1

公开(公告)日：2018-03-08

申请号：US15672584

申请日：2017-08-09

Applicant: ROLLS-ROYCE plc

Inventor： Benjamin J KEELER

IPC: F02C7/16

CPC classification number: F02C7/16 ,  F01D25/10 ,  F02C7/14 ,  F02C7/18 ,  F02C7/22 ,  F05D2220/32 ,  F05D2220/76 ,  F05D2260/213 ,  F05D2260/606 ,  F05D2270/112 ,  F05D2270/303

Abstract: An oil cooling system for an engine includes an oil input line configured to receive heated oil from a component, an oil cooler configured to cool oil and direct oil to an oil return line and a first bypass line configured to selectively bypass oil from the input line to the return line without passing through the oil cooler. The first bypass line includes a first oil pressure actuated valve urged toward a closed position, and configured to move toward an open position where a pressure differential across the valve exceeds first predetermined pressure. The first bypass line further includes a second oil pressure actuated valve urged toward an open position, and configured to move toward a closed position where pressure differential across the valve exceeds a second predetermined pressure. The second predetermined pressure is greater than first predetermined pressure, and the first and second valves are provided in series.