公开(公告)号：EP4202436A1

公开(公告)日：2023-06-28

申请号：EP22209100.1

申请日：2022-11-23

申请人： Rolls-Royce plc

发明人： Swann, Peter ,  Beaven, David M ,  Bemment, Craig W ,  Hobday, Alastair G ,  Keeler, Benjamin J ,  Madden, Christopher P ,  Yates, Martin K

IPC分类号： G01N33/28

摘要： The present application discloses a method (1030) of determining one or more fuel characteristics of an aviation fuel (F) for powering a gas turbine engine (10) of an aircraft (1). The method comprises: measuring (1031) one or more trace substance parameters of the fuel (F), the one or more trace substance parameters each associated with a respective trace substance in the fuel (F); and
determining (1032) one or more fuel characteristics of the fuel (F) based on the one or more trace substance parameters. Also disclosed is a fuel characteristic determination system (126), a method (1065) of operating an aircraft (1), and an aircraft.

公开(公告)号：EP4202195A1

公开(公告)日：2023-06-28

申请号：EP22209108.4

申请日：2022-11-23

申请人： Rolls-Royce plc

发明人： Keeler, Benjamin J ,  Beaven, David M ,  Bemment, Craig W ,  Ferra, Paul W ,  McNally, Kevin R ,  Minelli, Andrea ,  Yates, Martin K

IPC分类号： F02C3/20 ,  F02C9/28 ,  F02C9/40 ,  F01D21/00

摘要： A gas turbine engine of an aircraft forms part of a propulsion system, and comprises: a combustor arranged to combust the fuel and having an exit, and wherein a combustor exit temperature - T40 - is defined as an average temperature of flow at the combustor exit and a combustor exit pressure - P40 - is defined as the total pressure there; a turbine comprising a rotor having a leading edge and a trailing edge, and wherein a turbine rotor entry temperature - T41 - is defined as an average temperature of flow at the leading edge of the rotor of the turbine and a turbine rotor entry pressure - P41 - is defined as the total pressure there; and a compressor having an exit, wherein a compressor exit temperature - T30 - is defined as an average temperature of flow at the exit from the compressor at cruise conditions and a compressor exit pressure - P30 - is defined as the total pressure there (all at cruise conditions). A method of determining at least one fuel characteristic of a fuel provided to the gas turbine engine comprises changing a fuel supplied to the gas turbine engine; and determining the at least one fuel characteristic of the fuel based on a change in a relationship between T30 or P30 and one of T40 and T41, or of P40 and P41, respectively.