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：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：US20230323820A1

公开(公告)日：2023-10-12

申请号：US17853191

申请日：2022-06-29

Applicant: ROLLS-ROYCE plc

Inventor： Peter SWANN ,  Craig W BEMMENT ,  Christopher P MADDEN

IPC: F02C9/26 ,  F02C7/22 ,  B64D27/10 ,  B64D37/30

CPC classification number: F02C9/26 ,  F02C7/22 ,  B64D27/10 ,  B64D37/30 ,  F05D2220/323

Abstract: A gas turbine engine for an aircraft, including: staged combustion system having pilot fuel injectors and main fuel injectors, staged combustion system being operable in pilot-only range of operation and pilot-and-main range of operation; and fuel delivery regulator arranged to control delivery of fuel to pilot and main fuel injectors. Fuel delivery regulator arranged to receive fuel from a first fuel source containing a first fuel having a first fuel characteristic and a second fuel source containing a second fuel having a different second fuel characteristic. The fuel delivery regulator is arranged to deliver fuel to the pilot fuel injectors during at least part of the pilot-only range of operation having a different fuel characteristic from fuel delivered to one or both of the pilot and main fuel injectors during at least part of the pilot-and-main range of operation. A method of operating a gas turbine engine is also disclosed.

公开(公告)号：US20200370511A1

公开(公告)日：2020-11-26

申请号：US16538873

申请日：2019-08-13

Applicant: ROLLS-ROYCE PLC

Inventor： Craig W BEMMENT

IPC: F02K3/04 ,  F02C3/073

Abstract: A gas turbine engine for an aircraft includes: an engine core with a turbine, a compressor, and a core shaft connecting the turbine and compressor, the engine core having an inlet upstream of the compressor and an outlet downstream of the turbine; a fan upstream of the engine core, the fan including a plurality of fan blades; a gearbox receiving an input from the core shaft and outputs drive to the fan to drive the fan at a lower rotational speed than the core shaft; and a nacelle surrounding the engine core defining a bypass duct and a bypass exhaust nozzle, wherein the gas turbine engine is configured such that an axial Mach number at the engine core inlet (which is less than around 0.7) multiplied by an axial Mach number of an exhaust airflow from the bypass exhaust nozzle is between around 0.30 to 0.56 at maximum take-off conditions.