-
公开(公告)号：US20240210035A1
公开(公告)日：2024-06-27
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.
-
公开(公告)号：US20240209799A1
公开(公告)日：2024-06-27
申请号：US18337568
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: F02C9/38 , F02C7/14 , F02C7/16 , F05D2260/213
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.
-
公开(公告)号：US20240209792A1
公开(公告)日：2024-06-27
申请号：US18211809
申请日：2023-06-20
Applicant: ROLLS-ROYCE PLC
Inventor： Christopher P. MADDEN , Craig W. BEMMENT , Andrew T. SMITH , Peter SWANN
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.
-
公开(公告)号：US20240209791A1
公开(公告)日：2024-06-27
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
CPC classification number: F23R3/28 , F02C7/222 , F02C7/264 , F05D2240/35
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.
-
公开(公告)号：US20240209784A1
公开(公告)日：2024-06-27
申请号：US18337491
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 , F02C3/06 , F02C6/20 , F02C7/18 , F05D2220/323 , F05D2260/213 , F05D2260/232
Abstract: A method of operating a gas turbine engine including an engine core including: a turbine, compressor, combustor, core shaft; fan; fan shaft; gearbox that receives input from the core shaft and outputs drive to the fan via the fan shaft; primary oil loop system that supplies oil to the gearbox; and heat exchange system, which includes an air-oil heat exchanger through which oil in the primary oil loop system flows; and a fuel-oil heat exchanger through which the oil and fuel flow so heat is transferred therebetween, wherein the system branches so oil flows along each branch and the exchangers are arranged in parallel on different branches of the system; and a modulation valve that allows the oil sent via each branch to be varied. The method includes controlling the heat exchange system to raise the fuel temperature to at least 135° C. on entry to the combustor at cruise conditions.
-
Patent Agency Ranking
公开(公告)号：US20240068414A1
公开(公告)日：2024-02-29
申请号：US18503750
申请日：2023-11-07
Applicant: ROLLS-ROYCE plc
Inventor： Paul FLETCHER , Peter SWANN
CPC classification number: F02C9/28 , F02C9/42 , F02C9/44 , F05D2220/323 , F05D2270/051 , F05D2270/311 , F05D2270/313
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.
-
公开(公告)号：US20230258136A1
公开(公告)日：2023-08-17
申请号：US18162964
申请日：2023-02-01
Applicant: ROLLS-ROYCE plc
Inventor： Peter SWANN
CPC classification number: F02C9/40 , F02C7/22 , F05D2220/323 , F05D2270/306
Abstract: A system comprises first and second first fuel stores, an engine arranged to produce mechanical power, a fuel distribution system arranged to deliver fuel from the first and second fuel stores to the engine, the first fuel delivered at a first mass flow rate, the second fuel delivered at a second mass flow rate, the first and second mass flow rates contributing to a total mass flow rate of fuel to the engine, and a control system arranged to increase the relative fraction of the total mass flow rate of fuel represented by the second mass flow rate during a period of acceleration of the engine, in order to control a surge margin of the engine. The second fuel is selected to have a higher specific energy than the first fuel and to release a greater mass of water per unit mass of fuel than the first fuel.
-
公开(公告)号：US20230258135A1
公开(公告)日：2023-08-17
申请号：US18162949
申请日：2023-02-01
Applicant: ROLLS-ROYCE plc
Inventor： Peter SWANN
CPC classification number: F02C9/40 , F02C7/22 , F05D2220/323 , F05D2270/053 , F05D2270/08 , F05D2270/303
Abstract: A system has first and second fuel stores for first and second fuels, an engine, a fuel distribution system, first and second flow rates of the fuel contributing to a total flow rate of fuel; and a controller for controlling the relative fractions of the total flow rate of fuel to the engine according to the required power output of the engine such that the relative fraction of the total flow rate of fuel to the engine represented by the second flow rate increases with increasing required power output of the engine. The fuels are selected such that using only the second fuel results in a lower engine temperature than using only the first fuel, for the same mechanical power and/or the second fuel has a lower specific energy than the first and/or the second fuel produces more water during combustion than the first fuel per unit of fuel energy.
-
公开(公告)号：US20230193835A1
公开(公告)日：2023-06-22
申请号：US17853074
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
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 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.
-
公开(公告)号：US20250012223A1
公开(公告)日：2025-01-09
申请号：US18888979
申请日：2024-09-18
Applicant: Rolls-Royce plc
Inventor： Peter SWANN , Christopher P. Madden , Craig W. Bemment
Abstract: A gas turbine engine includes a staged combustion system having pilot fuel injectors and main fuel injectors. A fuel delivery regulator controls delivery of fuel to the pilot and main fuel injectors, receives 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 second fuel characteristic. In a transition range of operation between the pilot-only and the pilot-and-main ranges of operation, fuel is delivered to both the pilot and main fuel injectors at a transition staging ratio different from the pilot-and-main staging ratio. The fuel delivery regulator delivers fuel to one or both the pilot and main fuel injectors during the transition range of operation having a different fuel characteristic from fuel delivered to one or both the pilot and main fuel injectors during at least part of the pilot-and-main range of operation.
-
-
-
-
-
-
-
-
-
Search Results
75
records
(took 0.025 seconds)
