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公开(公告)号：US12215635B2
公开(公告)日：2025-02-04
申请号：US18208077
申请日：2023-06-09
Applicant: ROLLS-ROYCE plc
Inventor： Peter Swann , Craig W Bemment , Christopher P Madden
Abstract: A gas turbine engine for an aircraft includes a staged combustion system having pilot fuel injectors and main fuel injectors. The gas turbine engine further includes a fuel delivery regulator arranged to control delivery of fuel to the pilot and main fuel injectors, and a fuel characteristic determination module configured to determine one or more fuel characteristics of the fuel being supplied to the staged combustion system. A controller is configured to determine a staging point defining the point at which the staged combustion system is switched between pilot-only operation and pilot-and-main operation, the staging point being determined based on the determined one or more fuel characteristics, the controller being configured to control the staged combustion system according to the determined staging point.
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公开(公告)号：US12098679B2
公开(公告)日：2024-09-24
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
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.
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公开(公告)号：US11988144B2
公开(公告)日：2024-05-21
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
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.
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公开(公告)号：US12152497B2
公开(公告)日：2024-11-26
申请号：US18328225
申请日：2023-06-02
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
Abstract: A method of determining one or more fuel characteristic of an aviation fuel suitable for powering a gas turbine engine of an aircraft is disclosed. The method includes: determining, during use of the gas turbine engine, one or more contrail parameters related to contrail formation by the gas turbine engine. The determining of the one or more contrail parameters includes performing a sensor measurement on a region behind the gas turbine engine in which a contrail is or can be formed. The method also includes determining one or more fuel characteristics of the fuel based on the one or more contrail parameters. A fuel characteristic determination system, a method of operating an aircraft and an aircraft are also disclosed.
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公开(公告)号：US11994072B1
公开(公告)日：2024-05-28
申请号：US18337559
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
CPC classification number: F02C7/224 , F02C7/14 , F02C7/18 , F02C7/232 , F02C9/28 , F05D2220/323 , F05D2260/213 , F05D2270/303
Abstract: A method of operating a gas turbine engine is disclosed, the gas turbine engine comprising an engine core comprising a combustor arranged to burn a fuel; a turbine, the turbine comprising a plurality of turbine blades; a compressor arranged to be used as a source of cooling air for the turbine blades; and an inducer arranged to accelerate and direct the cooling air onto the turbine blades and comprising a plurality of airflow passageways and a modulating valve arranged to control cooling air flow into a subset of the passageways; and a fuel management system arranged to provide the fuel to the combustor, the fuel having a sulphur content of less than 30 ppm. The fuel management system comprises two fuel-oil heat exchangers through which oil and the fuel flow. The method comprises using the modulating valve to adjust the cooling air flow based on turbine inlet temperature.
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Patent Agency Ranking
公开(公告)号：US11788477B1
公开(公告)日：2023-10-17
申请号：US17853494
申请日：2022-06-29
Applicant: ROLLS-ROYCE plc
Inventor： Peter Swann , Christopher P Madden , Craig W Bemment
CPC classification number: F02C9/40 , F02C9/28 , F05D2220/323 , F05D2270/08 , F05D2270/306 , F05D2270/31 , F05D2270/71
Abstract: An aircraft has first and second fuel sources containing fuels with different characteristics, and one or more gas turbine engines powered by the fuels and each having a staged combustion system having pilot and main fuel injectors and being operable in pilot-only and pilot-and-main ranges of operation. The gas turbine engines each have a fuel delivery regulator arranged to control fuel delivery to the pilot and main fuel injectors. The method includes: obtaining a proposed mission description; obtaining nvPM impact parameters for the gas turbine engines, the impact parameters being associated with each operating condition of the proposed mission; calculating an optimised set of one or more fuel characteristics for each flight condition of the proposed flight defined in the flight description based on the nvPM impact parameters; and determining a fuel allocation based on the optimised set of one or more fuel characteristics.
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公开(公告)号：US11708796B2
公开(公告)日：2023-07-25
申请号：US17853103
申请日：2022-06-29
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
CPC classification number: F02C9/28 , F05D2260/80 , F05D2270/303 , F05D2270/304 , F05D2270/708 , F23N2221/10
Abstract: The present application discloses a method of determining one or more fuel characteristics of an aviation fuel used for powering a gas turbine engine of an aircraft. The method comprises: determining one or more performance parameters of the gas turbine engine during a first time period of operation of the gas turbine engine; and determining one or more fuel characteristics of the fuel based on the one or more performance parameters. A method of operating an aircraft, a fuel characteristic determination system, and an aircraft are also disclosed.
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公开(公告)号：US12241629B2
公开(公告)日：2025-03-04
申请号：US17896442
申请日：2022-08-26
Applicant: ROLLS-ROYCE plc
Inventor： Peter Swann , Christopher P Madden
Abstract: A gas turbine engine comprising a variable geometry combustor having fuel injectors, a rich-burn zone, a quick-quench zone, and a lean-burn zone, and further comprising quench ports for admitting quench air to the quick-quench zone; a variable geometry airflow arrangement for the variable geometry combustor, which is configured to vary an airflow through the fuel injectors and/or the quench ports; and a control system configured to control the variable geometry airflow arrangement in dependence upon an airflow delivered to the combustor, a fuel flow to the fuel injectors, and a target index of soot emissions to control the quantity of soot produced by combustion.
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公开(公告)号：US12111055B2
公开(公告)日：2024-10-08
申请号：US18211622
申请日：2023-06-20
Applicant: ROLLS-ROYCE PLC
Inventor： Christopher P Madden , Craig W Bemment , Andrew T Smith , Peter Swann
CPC classification number: F23R3/28 , B64D27/10 , F02C7/264 , F05D2240/35
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.
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公开(公告)号：US12071894B2
公开(公告)日：2024-08-27
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
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.
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