公开(公告)号：US20240271566A1

公开(公告)日：2024-08-15

申请号：US18643441

申请日：2024-04-23

Applicant: ROLLS-ROYCE PLC

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

IPC: F02C7/14 ,  F02C7/06 ,  F02C7/10 ,  F02C7/224 ,  F02C7/36

CPC classification number: F02C7/14 ,  F02C7/06 ,  F02C7/10 ,  F02C7/224 ,  F02C7/36 ,  F05D2220/323 ,  F05D2260/205 ,  F05D2260/213 ,  F05D2260/98

Abstract: A gas turbine engine includes an engine core with a combustor; a turbine including turbine blades; a compressor as a source of cooling air for the turbine blades; and an inducer to accelerate and direct the cooling air onto the turbine blades, and a modulating valve to allow or block cooling air flow into a subset of airflow passageways of the inducer; and a fuel management system to provide fuel to the combustor. The fuel management system includes a primary fuel-oil heat exchanger and a secondary fuel-oil heat exchanger through which oil and the fuel flow, to transfer heat between the oil and the fuel. A method of operating the engine includes using the modulating valve to adjust the cooling air flow based on turbine inlet temperature; and transferring 200-600 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：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：US20240209779A1

公开(公告)日：2024-06-27

申请号：US18337519

申请日：2023-06-20

Applicant: ROLLS-ROYCE PLC

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

IPC: F02C7/14 ,  F02C7/06 ,  F02C7/10 ,  F02C7/224 ,  F02C7/36

CPC classification number: F02C7/14 ,  F02C7/06 ,  F02C7/10 ,  F02C7/224 ,  F02C7/36 ,  F05D2220/323 ,  F05D2260/205 ,  F05D2260/213 ,  F05D2260/98

Abstract: A method of operating a gas turbine engine including an engine core and turbine, a compressor, a combustor arranged to combust a fuel, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core; a fan shaft; a main gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft, the main gearbox including gears and journal bearings; a recirculating lubrication system arranged to supply oil to lubricate the gears and journal bearings, the lubrication system including a first oil tank arranged to supply oil to the gears and journal bearings and a second oil tank arranged to supply oil to the journal bearings only. The method includes, at cruise conditions: transferring 200-600 KJ/m3 of heat to the fuel from the oil through the heat exchange system so as to control the oil temperature.

公开(公告)号：US20240077036A1

公开(公告)日：2024-03-07

申请号：US18203993

申请日：2023-05-31

Applicant: ROLLS-ROYCE plc

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

IPC: F02C9/28 ,  B64D27/10 ,  B64D37/04 ,  G08G5/00

CPC classification number: F02C9/28 ,  B64D27/10 ,  B64D37/04 ,  G08G5/0034

Abstract: A method of operating an aircraft including a gas turbine engine and a fuel tank arranged to provide fuel to the gas turbine engine. The method includes: determining at least one fuel characteristic of the fuel arranged to be provided to the gas turbine engine; and proposing or initiating a change to a flight profile of the aircraft based on the at least one fuel characteristic. For example, intended route and/or altitude of the aircraft may be changed based on the one or more fuel characteristics.

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：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：US20230313743A1

公开(公告)日：2023-10-05

申请号：US18328991

申请日：2023-06-05

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 ,  F05D2270/708 ,  F05D2270/304 ,  F05D2270/303 ,  F23N2221/10

Abstract: The present application provides 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 includes: passing UV-visual spectrum light through the fuel; measuring a transmittance parameter indicating the transmittance of light through the fuel; determining one or more fuel characteristics of the fuel based on the transmittance parameter; and communicating the one or more fuel characteristic to a control module of the gas turbine engine or the aircraft. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.

公开(公告)号：US20230193831A1

公开(公告)日：2023-06-22

申请号：US18096858

申请日：2023-01-13

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: F02C9/00 ,  B64D27/10 ,  B64D47/00 ,  G01N33/28 ,  G01N21/64 ,  G01N21/33 ,  G01N21/3577

CPC classification number: F02C9/00 ,  B64D27/10 ,  B64D47/00 ,  G01N33/287 ,  G01N21/64 ,  G01N21/33 ,  G01N21/3577 ,  G01N2021/3595

Abstract: A fuel characteristic determination system and method for determining one or more fuel characteristics of an aviation fuel for powering a gas turbine engine of an aircraft. The system includes a sensor component that is formed from a nitrile seal material and includes a surface that can be exposed to the fuel; a sensor for measuring a swell parameter of the seal material; and a fuel characteristics determination module for determining one or more fuel characteristics of the fuel based on the swell parameter. The method includes: exposing one or more seals of a fuel system of an aircraft to fuel within the fuel system; exposing a sensor component, made from the same material as the one or more seals, to the fuel; and measuring a swell parameter of the seal material.

公开(公告)号：US20220316410A1

公开(公告)日：2022-10-06

申请号：US17697761

申请日：2022-03-17

Applicant: ROLLS-ROYCE plc

Inventor： Peter SWANN ,  Jonathan E. HOLT

IPC: F02C9/28 ,  B64D37/30 ,  B64D27/16 ,  B64D31/00 ,  F02C3/22 ,  A01G15/00

Abstract: An aircraft propulsion system includes a hydrocarbon fuel store, a hydrogen fuel store, an engine system capable of producing thrust by combusting hydrocarbon fuel and/or combusting or oxidising hydrogen fuel, a conveying system to convey hydrocarbon and hydrogen fuel from the fuel stores to the engine system and a control system to control the respective flow rates of the fuel within the conveying system. The control system adapts the fractions of the total fuel energy flow rate to the engine system represented by the hydrocarbon and hydrogen fuel energy flow rates in order to reduce climate warming impact caused by at least one of carbon dioxide, water vapour and condensation trails and/or increase climate cooling impact caused by condensation trails produced by the aircraft propulsion system compared to a dual-fuel propulsion system in which a reserve of hydrocarbon fuel is entirely combusted before any of a reserve of hydrogen fuel.

公开(公告)号：US20210277839A1

公开(公告)日：2021-09-09

申请号：US17189663

申请日：2021-03-02

Applicant: ROLLS-ROYCE plc

Inventor： Christopher P. MADDEN ,  Peter SWANN

IPC: F02C9/40

Abstract: A gas turbine engine for an aircraft. The gas turbine comprises a combustor, a fuel injection system connected with a source of fuel and configured to inject fuel into the combustor, a water injection system connected with a source of water and which is configured to inject water into the combustor, and a control system. The control system is configured to identify an atmospheric condition; determine a water-fuel ratio for injection into the combustor of the gas turbine engine in response to the atmospheric condition; and control injection of fuel and water by the fuel injection system and the water injection system according to said water-fuel ratio to control an soot emissions caused by combustion of fuel therein.