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

IPC: F02C9/00 ,  F01D21/00 ,  F02C9/28

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.

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

IPC: F02C9/28 ,  B64D41/00 ,  B64D37/00 ,  B64D27/12

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


)


)



.