Aéronef

Abstract

Gas turbine engine (10) for an aircraft. The gas turbine engine comprising: a rich-burning, fast-cooling, lean-burning (RQL) combustor device (16) having a number of fuel spray nozzles (403, 404) in the range of 14 to 22 or a number of fuel spray nozzles per unit engine core size in the range of 2 to 6.A thrust-to-nvPM emission index ratio is defined as: Math [162] where: EIralient is the loss-corrected nvPM emission index in mg / kg of the gas turbine engine (10) when operating at approximately 7% of available thrust under given operating conditions; EImaxTO is the loss-corrected nvPM emission index in mg / kg of the gas turbine engine (10) when operating at approximately 100% of available thrust under given operating conditions; is the thrust of the gas turbine engine (10) at approximately 100% of available thrust in kN, is the thrust of the gas turbine engine (10) at approximately 7% of available thrust in kN; the thrust-to-nvPM emission index ratio is greater than 0.09; and the gas turbine engine (10) is designed to supply fuel including sustainable aviation fuel (SAF) to the fuel spray nozzles (403, 404).The invention also discloses a method of operating the gas turbine engine. [Fig. 6].