Patents Assigned to Roll-Royce plc
  • METHOD FOR SCANNING OF AN OBJECT IN A SCANNING APPARATUS
    Publication number: 20240219319
    Abstract: There is provided a method for scanning of an object in a scanning apparatus. The method comprises disposing the object on a support of the scanning apparatus, so that the object is positioned between an imaging beam emitting element and an imaging beam receiving element oppositely disposed to either side of the support. The support is rotatable relative to the emitting and receiving elements about an axis of rotation to allow creation of an image from projections each taken at a different relative angle of rotation. The object is positioned on the support so that a part to be scanned of the object is offset from the axis of rotation. The method further comprises operating the scanning apparatus at the multiple relative angles of rotation to produce an image of the offset object.
    Type: Application
    Filed: December 12, 2023
    Publication date: July 4, 2024
    Applicant: Rolls-Royce plc
    Inventor: Akhil MULLOTH
  • A GAS TURBINE AND GENERATOR ARRANGEMENT
    Publication number: 20240218804
    Abstract: A gas turbine and generator arrangement comprising a gas turbine engine (201) and a generator (207), the gas turbine engine comprising a turbine output shaft (319), characterised in that the gas turbine engine and the generator are horizontally or vertically spaced apart from each other in a lateral direction and a gearbox (325) translates the rotation of the turbine output shaft to drive a gearbox output shaft (329) which in turn drives the generator.
    Type: Application
    Filed: December 8, 2023
    Publication date: July 4, 2024
    Applicant: ROLLS-ROYCE PLC
    Inventor: Roy J. HARRON
  • Rectifier
    Patent number: 12027940
    Abstract: An AC to DC conversion device has first and second AC input terminals arranged to be coupled respectively to first and second terminals of a phase of an AC current generator, an H-bridge rectification device comprising two pairs of diodes, each pair being coupled to a respective one of the AC terminals to produce a DC output comprising a rectified back EMF waveform, and a waveform generator. The waveform generator comprises an output coupled to the DC output of the H-bridge rectification device, and is configured to input a unidirectional waveform to the DC output having the same magnitude and fundamental frequency as the rectified back EMF, phase shifted by a predetermined angle relative to the rectified back EMF waveform.
    Type: Grant
    Filed: July 11, 2022
    Date of Patent: July 2, 2024
    Assignee: ROLLS-ROYCE PLC
    Inventors: David R. Trainer, Ellis F H Chong, Jonathan M. Stevens
  • Cleaning system and a method of cleaning
    Patent number: 12025015
    Abstract: A cleaning system for cleaning gas paths in an engine core of a gas turbine engine includes a source of an engine cleaning liquid, an engine cleaning mist forming unit, a delivery device, a pump, and a mist collecting arrangement. The forming unit vapourises the cleaning liquid to form a cleaning mist and delivers the mist into the engine core. The delivery device delivers the cleaning liquid to the forming unit. The pump draws the mist through the engine core to clean the gas paths within the engine core. The mist collecting arrangement includes a condensing chamber, collects the mist that has passed through the engine core, and condenses the collected mist in the condensing chamber. The pump is arranged between and interconnects a rear engine core exhaust nozzle of the engine core and the condensing chamber.
    Type: Grant
    Filed: October 28, 2022
    Date of Patent: July 2, 2024
    Assignee: Rolls-Royce plc
    Inventors: Graeme E. Rigg, Timothy P. Aggas, David Munton
  • Gas turbine engine compression system with core compressor pressure ratio
    Patent number: 12024301
    Abstract: A gas turbine engine has a compression system radius ratio defined as the ratio of the radius of the tip of a fan blade to the radius of the tip of the most downstream compressor blade in the range of from 5 to 9. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.
    Type: Grant
    Filed: January 18, 2023
    Date of Patent: July 2, 2024
    Assignee: ROLLS-ROYCE plc
    Inventors: Gareth M Armstrong, Nicholas Howarth
  • GAS TURBINE ENGINE HEAT EXCHANGE
    Publication number: 20240209799
    Abstract: A method of operating a gas turbine engine including: a combustor arranged to combust a fuel; and a fuel management system arranged to provide the fuel to the combustor, wherein the fuel management system includes two fuel-oil heat exchangers through which oil and fuel flow, which are arranged to transfer heat between the oil and fuel and include primary and secondary fuel-oil heat exchangers; a fuel pump arranged to deliver the fuel to the combustor, wherein the fuel pump is located between the heat exchangers; and a recirculation valve located downstream of the primary heat exchanger, the recirculation valve arranged to allow a controlled amount of fuel which has passed through the primary heat exchanger to be returned to the inlet. The method includes selecting one or more fuels such that the calorific value of the fuel provided to the gas turbine engine is at least 43.5 MJ/kg.
    Type: Application
    Filed: June 20, 2023
    Publication date: June 27, 2024
    Applicant: ROLLS-ROYCE plc
    Inventors: Craig W. BEMMENT, Alastair G. HOBDAY, Benjamin J. KEELER, Christopher P. MADDEN, Andrea MINELLI, Andrew T. SMITH, Peter SWANN, Martin K. YATES
  • COMBUSTION OF FUEL
    Publication number: 20240209780
    Abstract: A method of operating a gas turbine engine, the engine including an engine core with a turbine, a compressor, a combustor arranged to combust a fuel, and a core shaft connecting the turbine to the compressor; a fan 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; a primary oil loop system to supply oil to lubricate the main gearbox; and a heat exchange system to transfer heat between the oil and the fuel, the oil having an average temperature of at least 180° C. on entry to the heat exchange system at cruise conditions. The method includes transferring heat from the oil to the fuel to lower the fuel viscosity to a value of less than or equal to 0.58 mm2/s on entry to the combustor at cruise conditions.
    Type: Application
    Filed: June 20, 2023
    Publication date: June 27, 2024
    Applicant: ROLLS-ROYCE PLC
    Inventors: Craig W. BEMMENT, Benjamin J. KEELER, Kevin R. MCNALLY, Andrea MINELLI
  • COMBUSTOR RE-LIGHT PROCEDURE
    Publication number: 20240210039
    Abstract: There is provided a method of operating a gas turbine engine. The gas turbine engine comprises a staged combustor having 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 transferring heat from the oil to the fuel before the fuel enters the combustor so as to lower the fuel viscosity to 0.58 mm2/s or lower on entry to the combustor at cruise conditions. Also disclosed is a gas turbine engine.
    Type: Application
    Filed: June 20, 2023
    Publication date: June 27, 2024
    Applicant: ROLLS-ROYCE PLC
    Inventors: Christopher P MADDEN, David M BEAVEN, Craig W BEMMENT, Paul W FERRA, Barani P GUNASEKARAN, Benjamin J KEELER, Peter SWANN, Martin K YATES
  • LEAN BURN COMBUSTION SYSTEM
    Publication number: 20240210038
    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 lower the fuel viscosity to 0.58 mm2/s or lower on entry to the combustor at cruise conditions.
    Type: Application
    Filed: June 20, 2023
    Publication date: June 27, 2024
    Applicant: ROLLS-ROYCE PLC
    Inventors: Christopher P MADDEN, Craig W BEMMENT, Paul W FERRA, Benjamin J KEELER, Andrea MINELLI, Peter SWANN, Martin K YATES
  • AIRCRAFT COMBUSTION SYSTEMS
    Publication number: 20240209792
    Abstract: A method of operating a gas turbine engine having a combustor having a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber. The fuel spray nozzles have 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 a fuel to the plurality of fuel spray nozzles having a calorific value of at least 43.5 MJ/kg. A gas turbine engine can be for an aircraft.
    Type: Application
    Filed: June 20, 2023
    Publication date: June 27, 2024
    Applicant: ROLLS-ROYCE PLC
    Inventors: Christopher P. MADDEN, Craig W. BEMMENT, Andrew T. SMITH, Peter SWANN
  • GAS TURBINE ENGINE AND METHOD OF OPERATING GAS TURBINE ENGINE
    Publication number: 20240209787
    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.
    Type: Application
    Filed: June 20, 2023
    Publication date: June 27, 2024
    Applicant: ROLLS-ROYCE plc
    Inventors: Craig W BEMMENT, Alastair G HOBDAY, Benjamin J KEELER, Christopher P MADDEN, Andrea MINELLI, Andrew T SMITH, Peter SWANN, Martin K YATES
  • FUEL OIL HEAT EXCHANGE
    Publication number: 20240209786
    Abstract: A method of operating a gas turbine engine is disclosed, the gas turbine engine comprising a fuel delivery system arranged to provide fuel; a combustor arranged to combust at least a proportion of the fuel; a primary fuel-oil heat exchanger arranged to have up to 100% of the fuel provided by the fuel delivery system flow therethrough; and a secondary fuel-oil heat exchanger arranged to have a proportion of the fuel from the primary fuel-oil heat exchanger flow therethrough. Fuel is arranged to flow from the primary fuel-oil heat exchanger to the secondary fuel-oil heat exchanger and oil is arranged to flow from the secondary fuel-oil heat exchanger to the primary fuel-oil heat exchanger. The method comprises transferring 200-600 KJ/m3 of heat to the fuel from the oil in the primary fuel-oil heat exchanger at cruise conditions.
    Type: Application
    Filed: June 20, 2023
    Publication date: June 27, 2024
    Applicant: ROLLS-ROYCE PLC
    Inventors: Craig W BEMMENT, Benjamin J KEELER, Kevin R MCNALLY, Andrea MINELLI
  • AIRCRAFT FUELLING
    Publication number: 20240210035
    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.
    Type: Application
    Filed: June 20, 2023
    Publication date: June 27, 2024
    Applicant: ROLLS-ROYCE PLC
    Inventors: Christopher P. MADDEN, Craig W. BEMMENT, Andrew T. SMITH, Peter SWANN
  • OIL SYSTEM
    Publication number: 20240209789
    Abstract: A method of operating a gas turbine engine having an engine core having a turbine, a compressor, a combustor 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 receiving an input from the core shaft and outputting drive to the fan via the fan shaft; a primary oil loop system to supply oil to lubricate the main gearbox; and a heat exchange system arranged to transfer heat between the oil and the fuel, the oil having an average temperature of at least 180° C. on entry to the heat exchange system at cruise conditions. The method includes transferring 200 to 600 KJ/m3 of heat from the oil to the fuel, using the heat exchange system, at cruise conditions, which may facilitate control of the oil temperature on entry to the main gearbox.
    Type: Application
    Filed: June 20, 2023
    Publication date: June 27, 2024
    Applicant: ROLLS-ROYCE plc
    Inventors: Craig W BEMMENT, Benjamin J KEELER, Kevin R MCNALLY, Andrea MINELLI
  • GAS TURBINE OPERATION
    Publication number: 20240209801
    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.
    Type: Application
    Filed: June 20, 2023
    Publication date: June 27, 2024
    Applicant: ROLLS-ROYCE plc
    Inventors: Christopher P. MADDEN, David M. BEAVEN, Craig W. BEMMENT, Paul W. FERRA, Benjamin J. KEELER, Peter SWANN, Martin K. YATES
  • AIRCRAFT HEAT MANAGEMENT
    Publication number: 20240209779
    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.
    Type: Application
    Filed: June 20, 2023
    Publication date: June 27, 2024
    Applicant: ROLLS-ROYCE PLC
    Inventors: Craig W. BEMMENT, Benjamin J. KEELER, Christopher P. MADDEN, Andrea MINELLI, Peter SWANN, Martin K YATES
  • SYSTEM AND METHOD FOR WET TREATMENT OF COMPONENT
    Publication number: 20240207901
    Abstract: A system for wet treatment of at least one component has a chamber configured to receive and at least partially enclose the at least one component. The system also has at least one component support, a plurality of tanks configured to store a corresponding plurality of fluids, at least one nozzle selectively fluidly coupled to the plurality of tanks and configured to spray a fluid towards the at least one component, at least one delivery valve for selectively fluidly coupling the at least one nozzle to the plurality of tanks, at least one port configured to collect the fluid sprayed by the at least one nozzle, and at least one recovery valve for selectively fluidly coupling the at least one port to the plurality of tanks.
    Type: Application
    Filed: December 1, 2023
    Publication date: June 27, 2024
    Applicant: ROLLS-ROYCE plc
    Inventor: Richard C. HARVEY
  • HEAT TRANSFER
    Publication number: 20240209785
    Abstract: A method of operating a gas turbine engine having an engine core having a 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 gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft; a heat exchange system having at least one fuel-oil heat exchanger arranged to transfer heat to the fuel; and a fuel pump arranged to deliver the fuel to the combustor, wherein the fuel pump is located downstream of the at least one fuel-oil heat exchanger. The method includes operating the gas turbine engine using a fuel having a lubricity of between 0.71 mm and 0.90 mm wear scar diameter (WSD) at 25° C.
    Type: Application
    Filed: June 20, 2023
    Publication date: June 27, 2024
    Applicant: ROLLS-ROYCE plc
    Inventors: Craig W. BEMMENT, Alastair G. HOBDAY, Benjamin J. KEELER, Andrea MINELLI, Andrew T. SMITH, Martin K. YATES
  • STAGED COMBUSTOR
    Publication number: 20240209791
    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.
    Type: Application
    Filed: June 20, 2023
    Publication date: June 27, 2024
    Applicant: Rolls-Royce plc
    Inventors: Christopher P. MADDEN, David M. BEAVEN, Craig W. BEMMENT, Paul W. FERRA, Barani P. GUNASEKARAN, Benjamin J. KEELER, Peter SWANN, Martin K. YATES
  • GAS TURBINE OPERATING CONDITIONS
    Publication number: 20240210037
    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.
    Type: Application
    Filed: June 20, 2023
    Publication date: June 27, 2024
    Applicant: ROLLS-ROYCE plc
    Inventors: Christopher P MADDEN, Craig W BEMMENT, Andrew T SMITH, Peter SWANN