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公开(公告)号：US11053842B2
公开(公告)日：2021-07-06
申请号：US16558417
申请日：2019-09-03
Applicant: ROLLS-ROYCE plc
Inventor： Craig W Bemment , Pascal Dunning
Abstract: An engine core including turbine, compressor, and core shaft connecting the turbine to the compressor, wherein a compressor exit temperature has an average airflow; and a fan upstream including a plurality of fan blades extending from a hub, each fan blade having a leading and trailing edge, wherein a fan rotor entry temperature has an average airflow across the leading edge of each blade at cruise conditions and fan tip rotor exit temperature has an average temperature of airflow across a radially outer portion of each blade at the trailing edge cruise conditions. A fan tip temperature rise as: the fan tip rotor exit temperature the fan rotor entry temperature . A core temperature rise as: the compressor exit temperature the fan rotor entry temperature , A core to fan tip temperature rise ratio of: the core temperature rise the fan tip temperature rise is in the range from 2.845-3.8.
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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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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：US12152496B2
公开(公告)日：2024-11-26
申请号：US18138333
申请日：2023-04-24
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 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 method comprises: determining, during use of the gas turbine engine, one or more exhaust content parameters by performing a sensor measurement on an exhaust of the gas turbine engine; and determining one or more fuel characteristics of the fuel based on the one or more exhaust parameters including the nvPM content of the exhaust. 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：US12078112B2
公开(公告)日：2024-09-03
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
IPC: G01N21/33 , B64D27/10 , B64D47/00 , F02C9/00 , G01N21/3577 , G01N21/64 , G01N33/28 , B64D37/00 , G01N21/35
CPC classification number: F02C9/00 , B64D27/10 , B64D47/00 , G01N21/33 , G01N21/3577 , G01N21/64 , G01N33/287 , B64D37/00 , 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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Patent Agency Ranking
公开(公告)号：US12018841B1
公开(公告)日：2024-06-25
申请号：US18211624
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 including a combustor. The combustor includes a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the chamber. The nozzles include a first and second subset of fuel spray nozzles. The combustor is operable in a condition wherein the first subset is supplied with more fuel than the second. A ratio of the number of nozzles in the first subset to the second is 1:2 to 1:5. The method includes operating the engine so a reduction of 20-80% in an average of particles/kg of nvPM in the exhaust when the engine is operating at 85% available thrust for given operating conditions and when the engine is operating at 30% is obtained when fuel provided to the nozzles is a sustainable aviation fuel instead of a fossil-based hydrocarbon fuel. Also, a gas turbine engine for an aircraft.
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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：US11780597B2
公开(公告)日：2023-10-10
申请号：US17853332
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
Abstract: A propulsion system for an aircraft comprises a gas turbine engine; a plurality of fuel tanks arranged to contain different fuels to be used to power the gas turbine engine, wherein the fuels have different calorific values; and a fuel manager. The fuel manager is arranged to store information on the fuel contained in each fuel tank and to control fuel input to the gas turbine engine in operation by selection of a specific fuel or fuel combination from one or more of the plurality of fuel tanks based on thrust demand of the gas turbine engine such that a fuel with a lower calorific value is supplied to the gas turbine engine at lower thrust demand.
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公开(公告)号：US11708769B2
公开(公告)日：2023-07-25
申请号：US17853405
申请日：2022-06-29
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: F01D21/003 , F02C9/28 , F05D2220/323 , F05D2260/80 , F05D2270/0831 , F05D2270/708 , F05D2270/804
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 method comprises: determining, during use of the gas turbine engine, one or more exhaust content parameters by performing a sensor measurement on an exhaust of the gas turbine engine; and determining one or more fuel characteristics of the fuel based on the one or more exhaust parameters. 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：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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