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公开(公告)号：US11643980B1
公开(公告)日：2023-05-09
申请号：US17853233
申请日：2022-06-29
Applicant: ROLLS-ROYCE plc
Inventor： Craig W Bemment , Benjamin J Keeler , Paul W Ferra , Alastair G Hobday , Kevin R McNally , Andrea Minelli , Martin K Yates
IPC: F02C9/28
CPC classification number: F02C9/28 , F05D2220/323 , F05D2270/30
Abstract: A method of determining a calorific value of fuel supplied to a gas turbine engine of an aircraft comprises sensing at least one engine parameter during a first time period of aircraft operation during which the gas turbine engine uses the fuel; and, based on the at least one sensed engine parameter, determining a calorific value of the fuel. The sensing may be repeated such that the at least one engine parameter is monitored over time. The gas turbine engine may be a propulsive gas turbine engine of the aircraft or a gas turbine engine of an auxiliary power unit of the aircraft.
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公开(公告)号：US12196133B1
公开(公告)日：2025-01-14
申请号：US18753092
申请日：2024-06-25
Applicant: ROLLS-ROYCE plc
Inventor： Andrea Minelli , Craig W Bemment , Benjamin J Keeler , Kevin R McNally , Martin K Yates
Abstract: A method of operating an aircraft gas turbine engine including: a core including a turbine, a compressor, a combustor to combust fuel, and a core shaft connecting the turbine to the compressor; a fan upstream of the core; a fan shaft; a bearing supporting the fan shaft; an oil loop system supplying oil to the bearing; and a heat exchange system including: an air-oil heat exchanger through which oil in the oil loop system flows; and a fuel-oil heat exchanger through which oil in the oil loop system and fuel flow to transfer heat between the oil and the fuel; and a bypass pipe to allow a proportion of the oil to flow past one of the air-oil and the fuel-oil heat exchanger; and a bypass valve to allow the proportion of the oil sent through the bypass pipe to be varied.
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公开(公告)号：US11643979B1
公开(公告)日：2023-05-09
申请号：US17853185
申请日：2022-06-29
Applicant: ROLLS-ROYCE plc
Inventor： Craig W Bemment , Benjamin J Keeler , Paul W Ferra , Alastair G Hobday , Kevin R McNally , Andrea Minelli , Martin K Yates
CPC classification number: F02C9/28 , B64D27/12 , B64D37/00 , B64D41/00 , F05D2220/323 , F05D2240/35 , F05D2270/313
Abstract: A propulsion system for an aircraft includes a gas turbine engine and a fuel tank, wherein the fuel includes at least a proportion of a sustainable aviation fuel—SAF—having a density between 90% and 98% of the density, ρK, of kerosene and a calorific value between 101% and 105% the calorific value CVK, of kerosene. The engine includes a combustor; and a fuel pump arranged to supply a fuel thereto at an energy flow rate, C, the pump being arranged to output fuel at a volumetric flow rate, Q, the percentage of fuel passing through the pump not provided to the combustor being referred to as a spill percentage. The fuel include X % SAF, where X % is in the range from 5% to 100%, and has a density, ρF, and a calorific value CVF. The propulsion system is arranged so:
the fuel-change spill ratio, Rs, of:
R
s
=
spill
percentage
at
cruise
using
kerosene
spill
percentage
at
cruise
using
the
fuel
with
X
%
S
A
F
is equal to:
Q
-
(
C
/
(
CV
K
×
ρ
K
)
)
Q
-
(
C
/
(
CV
F
×
ρ
F
)
)
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公开(公告)号：US12168957B2
公开(公告)日：2024-12-17
申请号：US18337603
申请日：2023-06-20
Applicant: ROLLS-ROYCE PLC
Inventor： Craig W Bemment , Benjamin J Keeler , Kevin R McNally , Andrea Minelli
Abstract: A method of operating a gas turbine engine is disclosed, the gas turbine engine comprising a fuel delivery system arranged to provide fuel; a combustor arranged to combust at least a proportion of the fuel; a primary fuel-oil heat exchanger arranged to have up to 100% of the fuel provided by the fuel delivery system flow therethrough; and a secondary fuel-oil heat exchanger arranged to have a proportion of the fuel from the primary fuel-oil heat exchanger flow therethrough. Fuel is arranged to flow from the primary fuel-oil heat exchanger to the secondary fuel-oil heat exchanger and oil is arranged to flow from the secondary fuel-oil heat exchanger to the primary fuel-oil heat exchanger. The method comprises 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：US12098675B2
公开(公告)日：2024-09-24
申请号：US18337546
申请日：2023-06-20
Applicant: ROLLS-ROYCE PLC
Inventor： Craig W Bemment , Benjamin J Keeler , Kevin R McNally , Andrea Minelli
CPC classification number: F02C7/14 , F02C7/36 , F23K5/20 , F05D2260/20 , F23K2300/204
Abstract: A method of operating a gas turbine engine, the engine including an engine core with a turbine, a compressor, a combustor arranged to combust a fuel, and a core shaft connecting the turbine to the compressor; a fan 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; a primary oil loop system to supply oil to lubricate the main gearbox; and a heat exchange system to transfer heat between the oil and the fuel, the oil having an average temperature of at least 180° C. on entry to the heat exchange system at cruise conditions. The method includes transferring heat from the oil to the fuel to lower the fuel viscosity to a value of less than or equal to 0.58 mm2/s on entry to the combustor at cruise conditions.
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Patent Agency Ranking
公开(公告)号：US11920514B1
公开(公告)日：2024-03-05
申请号：US18337749
申请日：2023-06-20
Applicant: ROLLS-ROYCE plc
Inventor： Craig W Bemment , Benjamin J Keeler , Kevin R McNally , Andrea Minelli
CPC classification number: F02C7/14 , F02C7/16 , F02C7/22 , F05D2260/213 , F05D2260/98
Abstract: A gas turbine engine including a fuel delivery system arranged to provide fuel; a combustor arranged to combust at least a proportion of the fuel; a primary fuel-oil heat exchanger arranged to have up to 100% of the fuel provided by the fuel delivery system flow therethrough; and a secondary fuel-oil heat exchanger arranged to have a proportion of the fuel from the primary fuel-oil heat exchanger flow therethrough. Fuel is arranged to flow from the primary fuel-oil heat exchanger to the secondary fuel-oil heat exchanger whereas oil is arranged to flow from the secondary fuel-oil heat exchanger to the primary fuel-oil heat exchanger. The method includes using at least one of the primary fuel-oil heat exchanger and the secondary fuel-oil heat exchanger to heat the fuel so as to adjust the fuel viscosity to a maximum of 0.58 mm2/s on entry to the combustor at cruise conditions.
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公开(公告)号：US12241423B2
公开(公告)日：2025-03-04
申请号：US18125431
申请日：2023-03-23
Applicant: ROLLS-ROYCE PLC
Inventor： Craig W Bemment , Benjamin J Keeler , Paul W Ferra , Alastair G Hobday , Kevin R McNally , Andrea Minelli , Martin K. Yates
Abstract: A method of refuelling an aircraft comprising a gas turbine engine and a fuel tank arranged to provide fuel to the gas turbine engine comprises obtaining an amount of energy required for an intended flight profile; obtaining a calorific value of fuel available to the aircraft for refuelling; calculating the amount of the available fuel needed to provide the required energy; and refuelling the aircraft with the calculated amount of the available fuel. The calculating the amount of the available fuel needed to provide the required energy may comprise obtaining an energy content of fuel already in the fuel tank and subtracting that from the determined amount of energy required for the intended flight profile.
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公开(公告)号：US12241422B2
公开(公告)日：2025-03-04
申请号：US18212290
申请日：2023-06-21
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: F02C9/28
Abstract: A method of determining at least one fuel characteristic of a fuel provided to a gas turbine engine of an aircraft includes making an operational change, the operational change being effected by a controllable component of a propulsion system of which the gas turbine engine forms a part, and being arranged to affect operation of the gas turbine engine, sensing a response to the operational change; and determining the at least one fuel characteristic based on the response to the operational change.
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公开(公告)号：US12241421B1
公开(公告)日：2025-03-04
申请号：US18753264
申请日：2024-06-25
Applicant: ROLLS-ROYCE PLC
Inventor： Andrea Minelli , Craig W Bemment , Benjamin J Keeler , David M Beaven , Kevin R McNally
Abstract: A method of operating a gas turbine engine comprising an engine core comprising a 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 gearbox that receives an input from the core shaft and outputs drive to the fan; an oil loop system arranged to supply oil to the gearbox; and a heat exchange system comprising an air-oil heat exchanger through which the oil flows, a fuel-oil heat exchanger through which the oil and the fuel flow; and a valve arranged to allow a proportion of the oil sent via at least one of the heat exchangers to be varied, is disclosed, the method comprising controlling the valve such that, under cruise conditions, an oil flow ratio of: rate of oil flow into air - oil heat exchanger rate of oil flow into fuel - oil heat exchanger is in the range from 0 to 0.59.
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公开(公告)号：US12163479B2
公开(公告)日：2024-12-10
申请号：US18125477
申请日：2023-03-23
Applicant: ROLLS-ROYCE PLC
Inventor： Craig W Bemment , Benjamin J Keeler , Paul W Ferra , Alastair G Hobday , Kevin R McNally , Andrea Minelli , Martin K Yates
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 gas turbine engine having a combustor supplied with fuel from a fuel system, the method comprising: determining a mass of the fuel being supplied to the combustor; determining a corresponding volume of the fuel being supplied to the combustor; and determining one or more fuel characteristics based on the determined mass and volume. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.
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