US 12,085,029 B2
Propulsion system control
Peter Swann, Derby (GB); Craig W Bemment, Derby (GB); Alastair G Hobday, Derby (GB); Benjamin J Keeler, Derby (GB); and Christopher P Madden, Derby (GB)
Assigned to ROLLS-ROYCE plc, London (GB)
Filed by ROLLS-ROYCE plc, London (GB)
Filed on Dec. 19, 2022, as Appl. No. 18/084,083.
Application 18/084,083 is a continuation of application No. 17/853,291, filed on Jun. 29, 2022, granted, now 11,585,282.
Claims priority of application No. 2118653 (GB), filed on Dec. 21, 2021.
Prior Publication US 2023/0193838 A1, Jun. 22, 2023
This patent is subject to a terminal disclaimer.
Int. Cl. F02C 9/40 (2006.01); F01D 21/00 (2006.01); F02C 9/28 (2006.01)
CPC F02C 9/40 (2013.01) [F01D 21/003 (2013.01); F02C 9/28 (2013.01); F05D 2220/323 (2013.01); F05D 2260/83 (2013.01); F05D 2270/07 (2013.01); F05D 2270/71 (2013.01)] 17 Claims
OG exemplary drawing
 
1. A method of operating an aircraft comprising a propulsion system, the propulsion system comprising a gas turbine engine and a fuel tank arranged to provide fuel to the gas turbine engine, the method comprising:
supplying the fuel to the gas turbine engine;
determining one or more fuel characteristics of the fuel supplied to the gas turbine engine from performance of the gas turbine engine during at least one of taxi, take-off, and climb of the aircraft; and
controlling the propulsion system during cruise based on the one or more fuel characteristics that have been determined,
wherein the one or more fuel characteristics of the fuel are selected from the group consisting of:
i. percentage of sustainable aviation fuel in the fuel;
ii. aromatic hydrocarbon content of the fuel;
iii. multi-aromatic hydrocarbon content of the fuel;
iv. percentage of nitrogen-containing species in the fuel;
V. presence or percentage of a tracer species or trace element in the fuel;
vi. hydrogen to carbon ratio of the fuel;
vii. hydrocarbon distribution of the fuel;
viii. level of non-volatile particulate matter emissions on combustion;
ix. naphthalene content of the fuel;
X. sulphur content of the fuel;
xi. cycloparaffin content of the fuel;
xii. oxygen content of the fuel;
xiii. thermal stability of the fuel;
xiv. level of coking of the fuel;
XV. an indication that the fuel is a fossil fuel; and
xvi. at least one of density, viscosity, calorific value, and heat capacity.
 
14. A propulsion system for an aircraft comprising:
a gas turbine engine;
a fuel tank arranged to contain a fuel to be supplied to the gas turbine engine;
a propulsion system controller arranged to:
determine one or more fuel characteristics of the fuel supplied to the gas turbine engine from performance of the gas turbine engine during at least one of taxi, take-off, and climb of the aircraft; and
control the propulsion system during cruise based on the one or more fuel characteristics that have been determined,
wherein the one or more fuel characteristics of the fuel are selected from the group consisting of:
i. percentage of sustainable aviation fuel in the fuel;
ii. aromatic hydrocarbon content of the fuel;
iii. multi-aromatic hydrocarbon content of the fuel;
iv. percentage of nitrogen-containing species in the fuel;
V. presence or percentage of a tracer species or trace element in the fuel;
vi. hydrogen to carbon ratio of the fuel;
vii. hydrocarbon distribution of the fuel;
viii. level of non-volatile particulate matter emissions on combustion;
ix. naphthalene content of the fuel;
X. sulphur content of the fuel;
xi. cycloparaffin content of the fuel;
xii. oxygen content of the fuel;
xiii. thermal stability of the fuel;
xiv. level of coking of the fuel;
XV. an indication that the fuel is a fossil fuel; and
xvi. at least one of density, viscosity, calorific value, and heat capacity.