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公开(公告)号：US20230332548A1
公开(公告)日：2023-10-19
申请号：US18208077
申请日：2023-06-09
Applicant: ROLLS-ROYCE plc
Inventor： Peter SWANN , Craig W BEMMENT , Christopher P MADDEN
CPC classification number: F02C9/26 , B64D27/10 , F02C7/22 , B64D37/30 , F05D2220/323
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：US20230313701A1
公开(公告)日：2023-10-05
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
CPC classification number: F01D21/003 , F02C9/28 , F05D2220/323 , F05D2270/804 , F05D2270/0831 , F05D2270/708 , F05D2260/80
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：US20230296060A1
公开(公告)日：2023-09-21
申请号：US18324619
申请日：2023-05-26
Applicant: ROLLS-ROYCE plc
Inventor： Peter SWANN , Craig W BEMMENT , Alastair G HOBDAY , Benjamin J KEELER , Christopher P MADDEN
CPC classification number: F02C9/28 , B64D37/04 , G08G5/0034 , B64D27/10
Abstract: A method of operating an aircraft including a gas turbine engine and a plurality of fuel tanks arranged to provide fuel to the gas turbine engine. At least two of the fuel tanks contain fuels with different fuel characteristics. The method includes obtaining a flight profile for a portion of a flight of the aircraft; and determining a fueling schedule for the portion of the flight based on the flight profile and the fuel characteristics, the fueling schedule governing the variation with time of how much fuel is drawn from each tank. Fuel input to the gas turbine engine may then be controlled in operation in accordance with the fueling schedule.
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公开(公告)号：US20230279808A1
公开(公告)日：2023-09-07
申请号：US18164858
申请日：2023-02-06
Applicant: ROLLS-ROYCE PLC
Inventor： Peter SWANN
CPC classification number: F02C6/20 , B64D27/02 , F02C9/28 , F02C9/42 , B64D2027/026 , F05D2220/323 , F05D2220/76 , F05D2270/08
Abstract: An aircraft propulsion system includes first and second engines and first and second electrical machines coupled to the first and second engines respectively. The first electrical machine is arranged to be driven by electrical power in order to at least partially drive the first engine. The second electrical machine is arranged to be driven by the second engine to generate electrical power. An electrical network allows transmission of electrical power between the electrical machines. A controller is arranged to selectively reduce fuel flow to the first engine and provide electrical power from the second electrical machine to the first electrical machine to drive the first electrical machine, based on expected properties of contrails formed in an exhaust plume of the first engine and/or the second engine. The system allows the formation of contrails by the engines to be managed in order to mitigate climate-warming effects of the contrails.
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公开(公告)号：US20230258101A1
公开(公告)日：2023-08-17
申请号：US18138333
申请日：2023-04-24
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: F01D21/003 , F02C9/28 , F05D2270/0831 , F05D2270/804 , F05D2260/80 , F05D2220/323 , F05D2270/708
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 method comprises: determining, during use of the gas turbine engine, one or more exhaust content parameters by performing a sensor measurement on an exhaust of the gas turbine engine; and determining one or more fuel characteristics of the fuel based on the one or more exhaust parameters including the nvPM content of the exhaust. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.
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Patent Agency Ranking
公开(公告)号：US20230192303A1
公开(公告)日：2023-06-22
申请号：US17853332
申请日：2022-06-29
Applicant: ROLLS-ROYCE plc
Inventor： Peter SWANN , Craig W. BEMMENT , Alastair G. HOBDAY , Benjamin J. KEELER , Christopher P. MADDEN
Abstract: A propulsion system for an aircraft comprises a gas turbine engine; a plurality of fuel tanks arranged to contain different fuels to be used to power the gas turbine engine, wherein the fuels have different calorific values; and a fuel manager. The fuel manager is arranged to store information on the fuel contained in each fuel tank and to control fuel input to the gas turbine engine in operation by selection of a specific fuel or fuel combination from one or more of the plurality of fuel tanks based on thrust demand of the gas turbine engine such that a fuel with a lower calorific value is supplied to the gas turbine engine at lower thrust demand.
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公开(公告)号：US20230184179A1
公开(公告)日：2023-06-15
申请号：US17941358
申请日：2022-09-09
Applicant: ROLLS-ROYCE plc
Inventor： Peter SWANN , Kevin M BRITCHFORD
CPC classification number: F02C9/42 , F02C9/28 , F05D2220/323 , F05D2270/051 , F05D2270/333 , F05D2270/335 , F05D2270/71 , F05D2270/053 , B64D2027/026
Abstract: An aircraft propulsion system comprises first and second thrust producing gas turbine engines. The system comprises a controller configured to determine a required overall propulsion system thrust level, and determine an engine core power level contribution from each aircraft gas turbine engine such that the overall propulsion system produces a minimum overall noise level and meets the required overall propulsion system thrust level. In meeting the minimum overall noise level, at least the first and second gas turbine engines are operated at different engine core power settings.
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公开(公告)号：US20230080006A1
公开(公告)日：2023-03-16
申请号：US17896467
申请日：2022-08-26
Applicant: ROLLS-ROYCE plc
Inventor： Peter SWANN , Christopher P MADDEN
IPC: F02C9/48
Abstract: A gas turbine engine comprising a variable geometry combustor having pilot fuel injectors and main fuel injectors; a fuel metering system configured to control fuel flow to the pilot fuel injectors and the main fuel injectors; a variable geometry airflow arrangement for the variable geometry combustor, which is configured to vary the airflow through the pilot fuel injectors and/or the main fuel injectors; a control system configured to control the variable geometry airflow arrangement in dependence upon airflow delivered to the combustor, the fuel flow to the pilot fuel injectors and the main fuel injectors, and a target index of soot emissions, thereby controlling airflow through the pilot fuel injectors and/or the main fuel injectors and hence the quantity of soot produced by combustion.
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公开(公告)号：US20230072621A1
公开(公告)日：2023-03-09
申请号：US17896442
申请日：2022-08-26
Applicant: ROLLS-ROYCE plc
Inventor： Peter SWANN , Christopher P MADDEN
IPC: F02C9/54
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：US20220403790A1
公开(公告)日：2022-12-22
申请号：US17829896
申请日：2022-06-01
Applicant: ROLLS-ROYCE plc
Inventor： Paul FLETCHER , Peter SWANN
Abstract: A method of mitigating contrails produced by an aircraft having a set of gas turbine engines, comprises the steps of (i) for each engine in a first subset of the engines, reducing the operating efficiency of the engine to produce a reduction in thrust provided by that engine and (ii) for each engine in a second subset, increasing the fuel flow to the engine to increase the thrust provided by that engine, the set of at least two gas turbine engines consisting of the first and second subsets. The method provides for contrail mitigation action by means of engine operating efficiency reduction to be directed to a first subset of engines for which contrail mitigation per unit engine operating efficiency reduction is greatest, the resulting reduction in thrust provided by such engines being at least partially compensated by increasing fuel flow to engines of the second subset.
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