Gas turbine combustion chamber with multiple fuel injector arrays

A combustion chamber for a gas turbine engine, the combustion chamber having a generally annular configuration about a central axis and having an outlet and being defined by inner and outer axial walls and an upstream end wall extending between the inner and outer walls, comprising:

• a) a plurality of first fuel injectors to inject first sprays of fuel directly into the combustion chamber during a first operational mode of a gas turbine engine, the plurality of first fuel injectors arranged in inner and outer first fuel injector arrays about the central axis, the first fuel injectors of each array being circumferentially spaced apart and located such that the first fuel injectors of one first fuel injector array are disposed circumferentially between first fuel injectors of the other first fuel injector array;
• b) a plurality of second fuel injectors to inject second sprays of fuel into the combustion chamber during a second operational mode of the gas turbine engine, the plurality of second fuel injectors arranged in inner and outer second fuel injector arrays about the central axis, the second fuel injector of each array being circumferentially spaced apart and located such that the second fuel injectors of one second fuel injector array are disposed circumferentially between second fuel injectors of the other second fuel injector array and
• c) first wall means extending axially into the combustion Chamber from the upstream end wall and having side edges attached to one of the inner and outer walls so as to define a plurality of chambers into which only the second fuel injectors inject fuel.