An injector assembly 10 for injecting propellants into a fluid fueled rocket engine. Injection assembly 10 comprises a plate member 12 with an opening 16 therethrough. Injector element 14 is sealed within opening 16. Oxidizer flows through central bore 18 and through orifices 26 into combustion chamber 27. Fuel flows from passageway 34 into an annular manifold 38 formed at an interface between flanged portion 32 and plate member 12. Fuel is then injected through orifices 42 into combustion chamber 27 where it impinges with the oxidizer at predetermined points in the combustion chamber 27.