초록 ▼

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 cham

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.

대표청구항 ▼

In a fluid fueled rocket engine including an injector assembly for injecting first and second liquid propellants into a combustion chamber, the improvement to the injector assembly comprising: a substantially solid one-piece plate member having an upstream face in fluid communication with a source o

In a fluid fueled rocket engine including an injector assembly for injecting first and second liquid propellants into a combustion chamber, the improvement to the injector assembly comprising: a substantially solid one-piece plate member having an upstream face in fluid communication with a source of said first propellant and a downstream face adjacent a combustion chamber, said plate member having an open extending therethrough from the upstream face to said downstream face, said plate member further including a narrow fluid passageway having a first end in fluid communication with a source of said second propellant and a second end in fluid communication with said opening; and a substantially solid injector element located in said opening in said plate member having an outer periphery in sealing engagement therewith, said injector element including a first propellant injection passageway having an upstream end in fluid communication with the source of said first propellant and at least one downstream end in fluid communication with said combustion chamber, said injector element further including a plurality of second propellant injection passageways having diameters in a range between 0.004 and 0.200 inches, each having an upstream end in fluid communication with the second end of said fluid passageway in said plate member and a downstream end in fluid communication with said combustion chamber; said first and second propellant injection passageways being angularly disposed to provide for impingement of said propellants upon one another at predetermined points in said combustion chamber.