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公开(公告)号：US12098677B2
公开(公告)日：2024-09-24
申请号：US18337497
申请日：2023-06-20
Applicant: ROLLS-ROYCE plc
Inventor： Craig W Bemment , Alastair G Hobday , Benjamin J Keeler , Andrea Minelli , Andrew T Smith , Martin K Yates
CPC classification number: F02C7/224 , F02C7/14 , F02C7/32 , F05D2260/20
Abstract: A method of operating a gas turbine engine having an engine core having 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 fan shaft; a gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft; a heat exchange system having at least one fuel-oil heat exchanger arranged to transfer heat to the fuel; and a fuel pump arranged to deliver the fuel to the combustor, wherein the fuel pump is located downstream of the at least one fuel-oil heat exchanger. The method includes operating the gas turbine engine using a fuel having a lubricity of between 0.71 mm and 0.90 mm wear scar diameter (WSD) at 25° C.
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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：US11994072B1
公开(公告)日：2024-05-28
申请号：US18337559
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: F02C7/224 , F02C7/14 , F02C7/18 , F02C7/232 , F02C9/28 , F05D2220/323 , F05D2260/213 , F05D2270/303
Abstract: 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.
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公开(公告)号：US11946417B2
公开(公告)日：2024-04-02
申请号：US18096146
申请日：2023-01-12
Applicant: ROLLS-ROYCE plc
Inventor： Andrea Minelli
CPC classification number: F02C7/16 , F02C3/06 , F02C7/06 , F02C7/22 , F05D2220/323 , F05D2240/35 , F05D2260/213 , F05D2260/232 , F05D2260/98
Abstract: A combination of a gas turbine engine and power electronics, includes an engine core and oil circuit to cool and lubricate bearings of the engine core, and a fuel circuit for supplying fuel to the combustor. The fuel circuit includes a low pressure pump for pressurising the fuel to a low pressure, and a high pressure pump to receive the low pressure fuel and increase the pressure to a high pressure for supply to a fuel metering system and the combustor. The engine includes a fuel-oil heat exchanger having a fuel side on the fuel circuit between an outlet of the low pressure pump and an inlet of the high pressure pump, and an oil side on the oil circuit to transfer heat from the oil circuit to the fuel circuit. The power electronics transfers heat to a cooling flow formed by a portion of the low pressure fuel.
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公开(公告)号：US12241415B1
公开(公告)日：2025-03-04
申请号：US18753128
申请日：2024-06-25
Applicant: ROLLS-ROYCE plc
Inventor： Benjamin J Keeler , Craig W Bemment , Andrea Minelli , Alastair G Hobday , Andrew T Smith
Abstract: A method of operating a gas turbine engine includes an engine core with a turbine, compressor, fuel combustor, and core shaft; a fan 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 supplying oil to the gearbox; and a heat exchange system including: air-oil and fuel-oil heat exchangers, and wherein the oil loop system branches such that part of the oil flows along each branch and the air-oil and fuel-oil heat exchangers are parallel on different branches; and a modulation valve allows the oil sent via each branch to be varied, the method including controlling the heat exchange system wherein, under cruise conditions, a heat transfer ratio of: rate of heat transfer from oil to air rate of heat transfer from oil to fuel is in the range from 0 to 0.67.
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Patent Agency Ranking
公开(公告)号：US12158115B2
公开(公告)日：2024-12-03
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
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.
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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：US12006872B1
公开(公告)日：2024-06-11
申请号：US18337497
申请日：2023-06-20
Applicant: ROLLS-ROYCE plc
Inventor： Craig W Bemment , Alastair G Hobday , Benjamin J Keeler , Andrea Minelli , Andrew T Smith , Martin K Yates
CPC classification number: F02C7/224 , F02C7/14 , F02C7/32 , F05D2260/20
Abstract: A method of operating a gas turbine engine having an engine core having 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 fan shaft; a gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft; a heat exchange system having at least one fuel-oil heat exchanger arranged to transfer heat to the fuel; and a fuel pump arranged to deliver the fuel to the combustor, wherein the fuel pump is located downstream of the at least one fuel-oil heat exchanger. The method includes operating the gas turbine engine using a fuel having a lubricity of between 0.71 mm and 0.90 mm wear scar diameter (WSD) at 25° C.
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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：US12270338B2
公开(公告)日：2025-04-08
申请号：US18169667
申请日：2023-02-15
Applicant: ROLLS-ROYCE plc
Inventor： Andrea Minelli
Abstract: A gas turbine engine for an aircraft includes: an engine core; fan; turbomachinery bearings; power gearbox; and a heat management system configured to provide lubrication and cooling to the power gearbox and turbomachinery bearings and including at least one air-lubricant heat exchanger to dissipate a first amount of heat to a first heat sink, and at least one fuel-lubricant heat exchanger to dissipate a second amount of heat to a second heat sink, wherein the heat management system is configured to provide a first proportion of heat generated by the power gearbox and the turbomachinery and dissipated to air at 85% of a core shaft maximum take-off speed in the range of 0.25 to 0.70, and a second proportion of heat generated by the power gearbox and the turbomachinery and dissipated to air at 65% of the core shaft maximum take-off speed in the range of 0.60 to 1.
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