are directed to the rotor blades of a turbine 22 a shaft 24 drivably connects the turbine 22 with air compressor fan 25 of compressor 16 from turbine 22 the combustion gases discharge rearwardly into an augmentor 26 and from there into the surrounding atmosphere through an exhaust nozzle 28 whereby the gas turbine engine 10 is provided with forward propulsive thrust combustor 20 is made up of inner and outer annular walls 30 and 32 which encompass an inner annular liner 34 and an outer annular liner 36 respectively liners 34 and 36 form an annular space therebetween which constitutes the combustion chamber 38 of combustor 20 fuel is supplied to the upstream end of combustion chamber 38 by the fuel injection system 12 of this invention so that the resulting fuel air mixture within the combustion chamber 38 can be ignited by any suitable igniter not shown located therein reference is now made to fig2 and 3 of the drawing for a detailed description of the fuel injection system 12 of this invention as shown in fig2 and 3 of the drawing fuel injection system 12 includes a plurality of plates 39 each plate 39 incorporates therein a pair of radially spaced apart tube shaped spray bars 42 and a plurality of rows of varying sized openings 44 this combination of components within each plate 39 will hereinafter be referred to as a segment 40 of injection system 12.