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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.
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公开(公告)号：US20240301829A1
公开(公告)日：2024-09-12
申请号：US18663599
申请日：2024-05-14
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：US11530652B2
公开(公告)日：2022-12-20
申请号：US17189663
申请日：2021-03-02
Applicant: ROLLS-ROYCE plc
Inventor： Christopher P. Madden , Peter Swann
Abstract: A gas turbine engine for an aircraft. The gas turbine comprises a combustor, a fuel injection system connected with a source of fuel and configured to inject fuel into the combustor, a water injection system connected with a source of water and which is configured to inject water into the combustor, and a control system. The control system is configured to identify an atmospheric condition; determine a water-fuel ratio for injection into the combustor of the gas turbine engine in response to the atmospheric condition; and control injection of fuel and water by the fuel injection system and the water injection system according to said water-fuel ratio to control an soot emissions caused by combustion of fuel therein.
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Patent Agency Ranking
公开(公告)号：US20240384689A1
公开(公告)日：2024-11-21
申请号：US18785965
申请日：2024-07-26
Applicant: ROLLS-ROYCE plc
Inventor： Peter SWANN , Christopher P. Madden , Craig W. Bemment
Abstract: 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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公开(公告)号：US20240263582A1
公开(公告)日：2024-08-08
申请号：US18634305
申请日：2024-04-12
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：US12152542B2
公开(公告)日：2024-11-26
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
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：US11821373B2
公开(公告)日：2023-11-21
申请号：US18053124
申请日：2022-11-07
Applicant: ROLLS-ROYCE plc
Inventor： Christopher P. Madden , Peter Swann
CPC classification number: F02C9/28 , F02C3/30 , F23R3/346 , F02C9/263 , F02C9/40 , F05D2270/08 , F05D2270/804
Abstract: A gas turbine engine for an aircraft. The gas turbine comprises a staged combustion system having pilot injectors and main injectors, a fuel metering system configured to control fuel flow to the pilot injectors and the main injectors, and a fuel system controller. The controller is configured to identify an atmospheric condition, determine a ratio of pilot fuel flow rate for the pilot injectors to main fuel flow rate for the main injectors in response to the atmospheric condition, and inject fuel by the pilot injectors and the main injectors in accordance with said ratio to control an index of soot emissions caused by combustion of fuel therein.
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公开(公告)号：US11530651B2
公开(公告)日：2022-12-20
申请号：US17189650
申请日：2021-03-02
Applicant: ROLLS-ROYCE plc
Inventor： Christopher P. Madden , Peter Swann
Abstract: A gas turbine engine for an aircraft. The gas turbine comprises a staged combustion system having pilot injectors and main injectors, a fuel metering system configured to control fuel flow to the pilot injectors and the main injectors, and a fuel system controller. The controller is configured to identify an atmospheric condition, determine a ratio of pilot fuel flow rate for the pilot injectors to main fuel flow rate for the main injectors in response to the atmospheric condition, and inject fuel by the pilot injectors and the main injectors in accordance with said ratio to control an index of soot emissions caused by combustion of fuel therein.
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