LIQUID PROPELLANT ROCKET ENGINE COAXIAL INJECTOR

To provide combustion stability in rocket engines over a wide range of thrust, a coaxial injector is provided which includes an outer annular sleeve for introduction of one propellant and a hollow pintle with spaced slots for introduction of another propellant to impinge on the first propellant. The...

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Bibliographische Detailangaben
1. Verfasser:	GERARD W. ELVERUM JR
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING COMBUSTION ENGINES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	To provide combustion stability in rocket engines over a wide range of thrust, a coaxial injector is provided which includes an outer annular sleeve for introduction of one propellant and a hollow pintle with spaced slots for introduction of another propellant to impinge on the first propellant. The slots are staggered in location and size to permit initial interlocking of the propellants and, therefore, increased mixing and combustion performance.