Combustion apparatus for a gas turbine engine

An aircraft comprising an engine system, the engine system comprising

• (a) a gas turbine engine including a combustion apparatus having a plurality of fuel injectors arranged in an annular array, each fuel injector of the plurality of fuel injectors having a fuel-emitting face comprising (1) a first set of fuel-emitting apertures arranged to emit fuel in a direction normal to a plane of the annular array and (2) a second set of fuel-emitting apertures arranged to emit fuel in a direction having an azimuthal component in the plane of the annular array directed towards the fuel-emitting face of an adjacent one of the plurality of fuel injectors, the azimuthal components all being the same for each second set of fuel-emitting apertures;
• and
• (b) a fuel system arranged to provide fuel to the first and second sets of fuel-emitting apertures of each fuel injector of the plurality of fuel injectors at a total fuel flow rate or a total chemical energy flow rate
• wherein each fuel-emitting face of the plurality of fuel injectors is in the plane of the annular array,
• the fuel system further comprises a controller arranged to receive one or more signals indicative of one or more of
• (i) starting of the gas turbine engine;
• (ii) flame-out of the combustion apparatus;
• and
• (iii) maneuvering of the aircraft associated with a risk of flame-out of the combustion apparatus, or preparation for such maneuvering, and
• in response to receipt of the one or more signals, the controller is further arranged to increase either
• (a) a proportion of the total fuel flow rate or the total chemical energy flow rate which is provided to the second sets of fuel-emitting apertures;
• or
• (b) a fuel flow rate or a chemical energy flow rate provided to the second sets of fuel-emitting apertures.