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公开(公告)号：US20190063369A1
公开(公告)日：2019-02-28
申请号：US16106853
申请日：2018-08-21
Applicant: ROLLS-ROYCE plc
Inventor： Benedict R. PHELPS , Mark J. WILSON , Gabriel GONZALEZ-GUTIERREZ , Nigel HS SMITH , Marco BARALE , Kashmir S. JOHAL , Stephane MM BARALON , Craig W. BEMMENT
Abstract: A gas turbine engine 10 is provided in which a fan having fan blades in which the camber distribution along the span allows the gas turbine engine to operate with improved efficiency when compared with conventional engines, whilst retaining an acceptable flutter margin.
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公开(公告)号：US20240271566A1
公开(公告)日：2024-08-15
申请号：US18643441
申请日：2024-04-23
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 gas turbine engine includes an engine core with a combustor; a turbine including turbine blades; a compressor as a source of cooling air for the turbine blades; and an inducer to accelerate and direct the cooling air onto the turbine blades, and a modulating valve to allow or block cooling air flow into a subset of airflow passageways of the inducer; and a fuel management system to provide fuel to the combustor. The fuel management system includes a primary fuel-oil heat exchanger and a secondary fuel-oil heat exchanger through which oil and the fuel flow, to transfer heat between the oil and the fuel. A method of operating the engine includes using the modulating valve to adjust the cooling air flow based on turbine inlet temperature; and transferring 200-600 kJ/m3 of heat to the fuel from the oil in the primary fuel-oil heat exchanger at cruise conditions.
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公开(公告)号：US20240209801A1
公开(公告)日：2024-06-27
申请号：US18337545
申请日：2023-06-20
Applicant: ROLLS-ROYCE plc
Inventor： Christopher P. MADDEN , David M. BEAVEN , Craig W. BEMMENT , Paul W. FERRA , Benjamin J. KEELER , Peter SWANN , Martin K. YATES
CPC classification number: F02C9/40 , F02C3/20 , F23R3/28 , F05D2240/35
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.
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公开(公告)号：US20240209779A1
公开(公告)日：2024-06-27
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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公开(公告)号：US20240175391A1
公开(公告)日：2024-05-30
申请号：US18405485
申请日：2024-01-05
Applicant: ROLLS-ROYCE plc
Inventor： Craig W. BEMMENT , Pascal DUNNING
CPC classification number: F02C3/04 , F02C7/36 , F02K3/06 , F05D2200/14 , F05D2220/323 , F05D2220/36 , F05D2240/307 , F05D2260/4031
Abstract: A gas turbine engine for an aircraft comprises an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor, wherein a compressor exit temperature is defined as an average temperature of airflow at the exit from the compressor;
and a fan located upstream of the engine core, the fan comprising a plurality of fan blades extending from a hub, each fan blade having a leading edge and a trailing edge, wherein a fan rotor entry temperature is defined as an average temperature of airflow across the leading edge of each fan blade at cruise conditions and a fan tip rotor exit temperature is defined as an average temperature of airflow across a radially outer portion of each fan blade at the trailing edge at cruise conditions. A core to fan tip temperature rise ratio is in the range from 2.845 to 3.8.-
Patent Agency Ranking
公开(公告)号：US20230313743A1
公开(公告)日：2023-10-05
申请号：US18328991
申请日：2023-06-05
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
IPC: F02C9/28
CPC classification number: F02C9/28 , F05D2260/80 , F05D2270/708 , F05D2270/304 , F05D2270/303 , F23N2221/10
Abstract: The present application provides 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 includes: passing UV-visual spectrum light through the fuel; measuring a transmittance parameter indicating the transmittance of light through the fuel; determining one or more fuel characteristics of the fuel based on the transmittance parameter; and communicating the one or more fuel characteristic to a control module of the gas turbine engine or the aircraft. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.
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公开(公告)号：US20230193834A1
公开(公告)日：2023-06-22
申请号：US17853117
申请日：2022-06-29
Applicant: ROLLS-ROYCE plc
Inventor： Benjamin J. KEELER , David M. BEAVEN , Craig W. BEMMENT , Paul W. FERRA , Kevin R. MCNALLY , Andrea MINELLI , Martin K. YATES
IPC: F02C9/22
CPC classification number: F02C9/22 , F05D2270/07 , F05D2270/309 , F05D2220/323
Abstract: A method of controlling a propulsion system of an aircraft, the propulsion system comprising a gas turbine engine arranged to be powered by a fuel and at least one variable inlet guide vane—VIGV, comprises obtaining at least one fuel characteristic of the fuel being provided to the gas turbine engine; and making a change to scheduling of the at least one VIGV based on the at least one obtained fuel characteristic.
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公开(公告)号：US20230193831A1
公开(公告)日：2023-06-22
申请号：US18096858
申请日：2023-01-13
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: F02C9/00 , B64D27/10 , B64D47/00 , G01N33/287 , G01N21/64 , G01N21/33 , G01N21/3577 , G01N2021/3595
Abstract: A fuel characteristic determination system and method for determining one or more fuel characteristics of an aviation fuel for powering a gas turbine engine of an aircraft. The system includes a sensor component that is formed from a nitrile seal material and includes a surface that can be exposed to the fuel; a sensor for measuring a swell parameter of the seal material; and a fuel characteristics determination module for determining one or more fuel characteristics of the fuel based on the swell parameter. The method includes: exposing one or more seals of a fuel system of an aircraft to fuel within the fuel system; exposing a sensor component, made from the same material as the one or more seals, to the fuel; and measuring a swell parameter of the seal material.
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公开(公告)号：US20210388772A1
公开(公告)日：2021-12-16
申请号：US17411617
申请日：2021-08-25
Applicant: ROLLS-ROYCE plc
Inventor： Craig W. BEMMENT
Abstract: A gas turbine engine for an aircraft and a method of operating a gas turbine engine on an aircraft. Embodiments disclosed include a gas turbine engine for an aircraft including: an engine core has a turbine, a compressor, and a core shaft; a fan located upstream of the engine core, the fan has a plurality of fan blades; a nacelle surrounding the engine core and defining a bypass duct and bypass exhaust nozzle; and a gearbox that receives an input from the core shaft and outputs drive to the fan wherein the gas turbine engine is configured such that a jet velocity ratio of a first jet velocity exiting from the bypass exhaust nozzle to a second jet velocity exiting from an exhaust nozzle of the engine core at idle conditions is greater by a factor of 2 or more than the jet velocity ratio at maximum take-off conditions.
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公开(公告)号：US20210301718A1
公开(公告)日：2021-09-30
申请号：US17196382
申请日：2021-03-09
Applicant: ROLLS-ROYCE plc
Inventor： Michael O. HALES , Craig W. BEMMENT , Benjamin J. SELLERS , Ian J. BOUSFIELD , Amarveer S. MANN
Abstract: A gas turbine engine (10) comprising:
a high pressure turbine (17);
a low pressure turbine (19);
a high pressure compressor (15) coupled to the high pressure turbine (17) by a high pressure shaft (27);
a propulsor (23) and a low pressure compressor (14) coupled to the low pressure turbine (19) via a low pressure shaft (26) and a reduction gearbox (30); wherein
the low pressure compressor (14) consists of four compressor stages (14) and defines a cruise pressure ratio of between 2.4:1 and 3.3:1;
the high pressure compressor (15) defines a cruise pressure ratio of less than 17:1; and
the high pressure compressor (15) and low pressure compressor (14) together define a cruise core overall pressure ratio of greater than 36:1.
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