公开(公告)号：US20250003592A1

公开(公告)日：2025-01-02

申请号：US18882197

申请日：2024-09-11

Applicant: ROLLS-ROYCE plc

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

IPC: F23R3/28 ,  B64D27/10 ,  F02C7/264

Abstract: A method of operating a gas turbine engine; the gas turbine engine includes a combustor. The combustor includes a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber. The plurality of fuel spray nozzles includes a first subset of fuel spray nozzles and a second subset of fuel spray nozzles. The combustor is operable in a condition in which the first subset of fuel spray nozzles are supplied with more fuel than the second subset of fuel spray nozzles. A ratio of the number of fuel spray nozzles in the first subset of fuel spray nozzles to the number of fuel spray nozzles in the second subset of fuel spray nozzles is in the range of 1:2 to 1:5. The method includes: providing fuel to the one or more fuel-oil heat exchangers. Also provided is a gas turbine engine for an aircraft.

公开(公告)号：US20230332543A1

公开(公告)日：2023-10-19

申请号：US18337516

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: F02C7/14 ,  F02C7/224 ,  F02C7/36

CPC classification number: F02C7/14 ,  F02C7/224 ,  F02C7/36 ,  F05D2220/323 ,  F05D2260/213

Abstract: A method of operating a gas turbine engine including an engine core including a turbine, compressor, combustor to combust a fuel, and core shaft connecting the turbine and compressor; a fan upstream of the engine core; a fan shaft; a 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 the gearbox; and a heat exchange system. The method includes controlling the heat exchange system to adjust fuel viscosity to be lower than or equal to 0.58 mm2/s on entry to the combustor at cruise conditions.

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：US20240418129A1

公开(公告)日：2024-12-19

申请号：US18421471

申请日：2024-01-24

Applicant: ROLLS-ROYCE PLC

Inventor： Christopher P MADDEN ,  Craig W BEMMRNT ,  Andrew T SMITH ,  Peter SWANN

IPC: F23R3/34 ,  F02C3/20 ,  F02C7/224 ,  F02C7/228 ,  F02C9/40 ,  F23R3/28

Abstract: There is provided a method of operating a gas turbine engine including a combustor. The combustor includes a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the chamber. The nozzles include a first and second subset of fuel spray nozzles. The combustor is operable in a condition wherein the first subset is supplied with more fuel than the second. A ratio of the number of nozzles in the first subset to the second is 1:2 to 1:5. The method includes operating the engine so a reduction of 20-80% in an average of particles/kg of nvPM in the exhaust when the engine is operating at 85% available thrust for given operating conditions and when the engine is operating at 30% is obtained when fuel provided to the nozzles is a sustainable aviation fuel instead of a fossil-based hydrocarbon fuel. Also provided is a gas turbine engine for an aircraft.

公开(公告)号：US20240210037A1

公开(公告)日：2024-06-27

申请号：US18211624

申请日：2023-06-20

Applicant: ROLLS-ROYCE plc

Inventor： Christopher P MADDEN ,  Craig W BEMMENT ,  Andrew T SMITH ,  Peter SWANN

IPC: F02C9/40 ,  F02C3/20 ,  F23R3/28

CPC classification number: F02C9/40 ,  F02C3/20 ,  F23R3/28 ,  F05D2240/35 ,  F05D2270/08

Abstract: A method of operating a gas turbine engine including a combustor. The combustor includes a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the chamber. The nozzles include a first and second subset of fuel spray nozzles. The combustor is operable in a condition wherein the first subset is supplied with more fuel than the second. A ratio of the number of nozzles in the first subset to the second is 1:2 to 1:5. The method includes operating the engine so a reduction of 20-80% in an average of particles/kg of nvPM in the exhaust when the engine is operating at 85% available thrust for given operating conditions and when the engine is operating at 30% is obtained when fuel provided to the nozzles is a sustainable aviation fuel instead of a fossil-based hydrocarbon fuel. Also, a gas turbine engine for an aircraft.