Kraftstoffeigenschaften

Details

Veröffentlichungs-Nr.

EP4664013

Aktenzeichen

EP25180938

Anmeldetag

5. Juni 2025

Veröffentlichung

17. Dezember 2025

Rechtsraum

EP

IPC

F23R3/34F02C7/228F02C9/40

Abstract

A gas turbine engine for an aircraft. The gas turbine engine (10) comprises: a combustor (16), comprising a combustion chamber (120) and a plurality of fuel spray nozzles (124) configured to inject fuel into the combustion chamber (120), wherein the plurality of fuel spray nozzles (124) comprises a first subset (124A) of fuel spray nozzles (124) and a second subset (124B) of fuel spray nozzles (124), wherein the combustor (16) is operable in a condition in which each of the fuel spray nozzles of the first subset (124A) of fuel spray nozzles (124) is supplied with fuel at a greater fuel flow rate than each of the fuel spray nozzles of the second subset (124B) of fuel spray nozzles (124), wherein a ratio of the number of fuel spray nozzles (124) in the first subset (124A) of fuel spray nozzles (124) to the number of fuel spray nozzles (124) in the second subset (124B) of fuel spray nozzles (124) is in the range of 1:3 to 1:6. An MTO nvPM emissions index ratio-modified fuel flow is defined as: EImaxTO,SAFEImaxTO,FF×Wf,maxTO where: EI_maxTO,SAF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine (10) when operating at around 100% available thrust for given operating conditions if a fuel provided to the plurality of fuel spray nozzles (124) comprises a sustainable aviation fuel (SAF); EI_maxTO,FF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine (10) when operating at around 100% available thrust for the given operating conditions if a fuel provided to the plurality of fuel spray nozzles (124) is a fossil-based hydrocarbon fuel; and W_f,maxTO is the mass flow rate of fuel provided to the plurality of fuel spray nozzles (124) in kg/s when the gas turbine engine (10) is operating at around 100% available thrust for the given operating conditions. The MTO nvPM emissions index ratio-modified fuel flow of the gas turbine engine (10) in kg/s is less than 4. The gas turbine engine (10) is configured to provide fuel comprising a SAF to the plurality of fuel spray nozzles (124). Also disclosed are methods of operating the gas turbine engine.

Anmelder

Firma

Rolls-Royce plc

Land

🇬🇧 Großbritannien

Fachgebiete