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公开(公告)号：US12098679B2
公开(公告)日：2024-09-24
申请号：US18337615
申请日：2023-06-20
Applicant: Rolls-Royce plc
Inventor： Christopher P Madden , David M Beaven , Craig W Bemment , Paul W Ferra , Barani P Gunasekaran , Benjamin J Keeler , Peter Swann , Martin K Yates
Abstract: There is provided a method of operating a gas turbine engine. The gas turbine engine comprises a staged combustor comprising an arrangement of fuel spray nozzles in which fuel flow is biased to a subset of the nozzles adjacent one or more ignitors during a re-light procedure. The method comprises providing fuel to the combustor having a calorific value of at least 43.5 MJ/kg. Also disclosed is a gas turbine engine.
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公开(公告)号：US11859565B2
公开(公告)日：2024-01-02
申请号：US17853333
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: F02C9/28
CPC classification number: F02C9/28 , F05D2220/323 , F05D2240/35 , F05D2270/303 , F05D2270/309 , F05D2270/3013
Abstract: A gas turbine engine includes: a combustor that combust the fuel and having an exit, a combustor exit temperature (T40) is the average temperature of flow and a combustor exit pressure (P40) is the total pressure there; a turbine including a rotor having a leading edge and a trailing edge, and wherein a turbine rotor entry temperature (T41) is an average temperature of flow at the leading edge and a turbine rotor entry pressure (P41) is the total pressure there; and a compressor having an exit, wherein a compressor exit temperature (T30) is the average temperature of flow at the exit from the compressor and a compressor exit pressure (P30) is the total pressure there (all at cruise conditions). A method of determining at least one fuel characteristic includes changing a fuel supplied to the engine; and determining a change in a relationship between T30 or P30, T40 and T41, or of P40 and P41, respectively.
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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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Patent Agency Ranking
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：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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公开(公告)号：US12158438B2
公开(公告)日：2024-12-03
申请号：US17853184
申请日：2022-06-29
Applicant: ROLLS-ROYCE PLC
Inventor： Craig W Bemment , Paul W Ferra , Alastair G Hobday , Benjamin J Keeler , Kevin R Mcnally , Andrea Minelli , Martin K Yates
Abstract: A method of checking refuelling of an aircraft comprising a gas turbine engine and a fuel tank arranged to provide fuel to the gas turbine engine comprises: receiving an input of calorific value data for fuel provided to the aircraft on refuelling; independently determining at least one of: (i) the calorific value of fuel supplied to the gas turbine engine in use; and (ii) the calorific value of the fuel provided to the aircraft on refuelling; and providing an alert if the determined calorific value is inconsistent with the calorific value data input received.
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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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