公开(公告)号：US20240209791A1

公开(公告)日：2024-06-27

申请号：US18337615

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: F23R3/28 ,  F02C7/22 ,  F02C7/264

CPC classification number: F23R3/28 ,  F02C7/222 ,  F02C7/264 ,  F05D2240/35

Abstract: There is provided a method of operating a gas turbine engine. The gas turbine engine comprises a staged combustor comprising 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 providing fuel to the combustor having a calorific value of at least 43.5 MJ/kg. Also disclosed is a gas turbine engine.

公开(公告)号：US20240209788A1

公开(公告)日：2024-06-27

申请号：US18337699

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: F02C7/224 ,  F02C7/22 ,  F02C7/232

CPC classification number: F02C7/224 ,  F02C7/222 ,  F02C7/232 ,  F05D2270/07

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 raise the fuel temperature to an average of at least 135° C. on entry to the combustor at cruise conditions. Also provided is a gas turbine for an aircraft.

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：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：US20240209801A1

公开(公告)日：2024-06-27

申请号：US18337545

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 ,  Martin K. YATES

IPC: F02C9/40 ,  F02C3/20 ,  F23R3/28

CPC classification number: F02C9/40 ,  F02C3/20 ,  F23R3/28 ,  F05D2240/35

Abstract: There is provided a method of operating a gas turbine engine, the gas turbine engine comprising: a rich burn, quick quench, lean burn (RQL) combustor having a number of fuel spray nozzles in the range 14-22 or a number of fuel spray nozzles per unit engine core size in the range 2 to 6. The method comprises operating the gas turbine engine such that a reduction of 10-70% in an average of particles/kg of nvPM in the exhaust of the gas turbine engine when the engine 10 is operating at 85% available thrust for given operating conditions and particles/kg of nvPM in the exhaust of the gas turbine engine when the engine is operating at 30% available thrust for the given operating conditions is obtained when a fuel provided to the combustor is a sustainable aviation fuel instead of a fossil-based hydrocarbon fuel.

公开(公告)号：US20230193834A1

公开(公告)日：2023-06-22

申请号：US17853117

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: F02C9/22

CPC classification number: F02C9/22 ,  F05D2270/07 ,  F05D2270/309 ,  F05D2220/323

Abstract: A method of controlling a propulsion system of an aircraft, the propulsion system comprising a gas turbine engine arranged to be powered by a fuel and at least one variable inlet guide vane—VIGV, comprises obtaining at least one fuel characteristic of the fuel being provided to the gas turbine engine; and making a change to scheduling of the at least one VIGV based on the at least one obtained fuel characteristic.