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1. 发明授权

US12098679B2 Staged combustor 有权
公开(公告)号：US12098679B2
公开(公告)日：2024-09-24
申请号：US18337615
申请日：2023-06-20
申请人： Rolls-Royce plc
发明人： Christopher P Madden , David M Beaven , Craig W Bemment , Paul W Ferra , Barani P Gunasekaran , Benjamin J Keeler , Peter Swann , Martin K Yates
IPC分类号： F02C7/262 , F23R3/34 , F02C7/22 , F02C7/264 , F02C9/46 , F23R3/28
CPC分类号： F02C7/262 , F23R3/343 , F02C7/222 , F02C7/264 , F02C9/46 , F23R3/28
摘要： 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.

2. 发明授权

US11988144B2 Fuel viscosity 有权
公开(公告)号：US11988144B2
公开(公告)日：2024-05-21
申请号：US18337516
申请日：2023-06-20
申请人： ROLLS-ROYCE plc
发明人： Craig W Bemment , Alastair G Hobday , Benjamin J Keeler , Christopher P Madden , Andrea Minelli , Andrew T Smith , Peter Swann , Martin K Yates
IPC分类号： F02C7/14 , F02C7/224 , F02C7/36
CPC分类号： F02C7/14 , F02C7/224 , F02C7/36 , F05D2220/323 , F05D2260/213
摘要： 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.

3. 发明授权

US11994072B1 Fuel management system 有权
公开(公告)号：US11994072B1
公开(公告)日：2024-05-28
申请号：US18337559
申请日：2023-06-20
申请人： ROLLS-ROYCE PLC
发明人： Craig W Bemment , Benjamin J Keeler , Christopher P Madden , Andrea Minelli , Peter Swann , Martin K Yates
IPC分类号： F02C7/224 , F02C7/14 , F02C7/18 , F02C7/232 , F02C9/28
CPC分类号： F02C7/224 , F02C7/14 , F02C7/18 , F02C7/232 , F02C9/28 , F05D2220/323 , F05D2260/213 , F05D2270/303
摘要： 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.

4. 发明授权

US11788477B1 Loading parameters 有权
公开(公告)号：US11788477B1
公开(公告)日：2023-10-17
申请号：US17853494
申请日：2022-06-29
申请人： ROLLS-ROYCE plc
发明人： Peter Swann , Christopher P Madden , Craig W Bemment
IPC分类号： F02C9/40 , F02C9/28
CPC分类号： F02C9/40 , F02C9/28 , F05D2220/323 , F05D2270/08 , F05D2270/306 , F05D2270/31 , F05D2270/71
摘要： 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.

5. 发明授权

US11708796B2 Performance parameters 有权
公开(公告)号：US11708796B2
公开(公告)日：2023-07-25
申请号：US17853103
申请日：2022-06-29
申请人： ROLLS-ROYCE plc
发明人： Peter Swann , David M Beaven , Craig W Bemment , Alastair G Hobday , Benjamin J Keeler , Christopher P Madden , Martin K Yates
IPC分类号： F02C9/00 , F02C9/28
CPC分类号： F02C9/28 , F05D2260/80 , F05D2270/303 , F05D2270/304 , F05D2270/708 , F23N2221/10
摘要： 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.

6. 发明授权

US12111055B2 Aircraft fuelling 有权
公开(公告)号：US12111055B2
公开(公告)日：2024-10-08
申请号：US18211622
申请日：2023-06-20
申请人： ROLLS-ROYCE PLC
发明人： Christopher P Madden , Craig W Bemment , Andrew T Smith , Peter Swann
IPC分类号： F23R3/28 , B64D27/10 , F02C7/264
CPC分类号： F23R3/28 , B64D27/10 , F02C7/264 , F05D2240/35
摘要： 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.

7. 发明授权

US12071894B2 Aircraft heat management 有权
公开(公告)号：US12071894B2
公开(公告)日：2024-08-27
申请号：US18337519
申请日：2023-06-20
申请人： ROLLS-ROYCE PLC
发明人： Craig W Bemment , Benjamin J Keeler , Christopher P Madden , Andrea Minelli , Peter Swann , Martin K Yates
IPC分类号： F02C7/14 , F02C7/06 , F02C7/10 , F02C7/224 , F02C7/36
CPC分类号： F02C7/14 , F02C7/06 , F02C7/10 , F02C7/224 , F02C7/36 , F05D2220/323 , F05D2260/205 , F05D2260/213 , F05D2260/98
摘要： 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.

8. 发明授权

US11815031B2 Fuelling schedule 有权
公开(公告)号：US11815031B2
公开(公告)日：2023-11-14
申请号：US17853074
申请日：2022-06-29
申请人： ROLLS-ROYCE PLC
发明人： Peter Swann , Craig W Bemment , Alastair G Hobday , Benjamin J Keeler , Christopher P Madden
IPC分类号： F02C9/28 , B64D37/04 , B64D27/10 , G08G5/00
CPC分类号： F02C9/28 , B64D27/10 , B64D37/04 , G08G5/0034
摘要： 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, where at least two of the fuel tanks contain fuels with different fuel characteristics. The method includes obtaining a flight profile for a flight of the aircraft; and determining a fuelling schedule for the flight based on the flight profile and the fuel characteristics. The fuelling schedule governs 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 fuelling schedule.

9. 发明授权

US11732659B2 Controlling soot 有权
公开(公告)号：US11732659B2
公开(公告)日：2023-08-22
申请号：US17896467
申请日：2022-08-26
申请人： ROLLS-ROYCE plc
发明人： Peter Swann , Christopher P Madden
IPC分类号： F02C9/50 , F02C9/16 , F23R3/34 , F23R3/26 , F23C7/00
CPC分类号： F02C9/50 , F02C9/16 , F23C7/008 , F23R3/26 , F23R3/343 , F05D2270/082
摘要： 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.

10. 发明授权

US11591973B1 Gas turbine operation 有权
公开(公告)号：US11591973B1
公开(公告)日：2023-02-28
申请号：US17853365
申请日：2022-06-29
申请人： ROLLS-ROYCE plc
发明人： Peter Swann , Christopher P Madden , Craig W Bemment
IPC分类号： F02C9/40 , F02C9/28
摘要： A aircraft gas turbine engine and operation method, the engine including: a staged combustion system having pilot and main fuel injectors, and operates in a pilot-only range wherein fuel delivers to pilot fuel injectors, and a pilot-and-main operation range wherein fuel is delivered to at least the main fuel injectors. The engine further includes a fuel delivery regulator to pilot and main fuel injectors, which receives fuel from a first and second source containing fuels each with different characteristics. The staged combustion system switches between pilot-only and pilot-and-main range operation when in steady cruise mode, the mode defining a boundary between first and second engine cruise operation range. The fuel delivery regulator delivers fuel to pilot fuel injectors during at least part of the first engine cruise operation with different fuel characteristics from fuel delivered to one or both pilot and main fuel injectors the second engine cruise operation range.

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