LIQUID PROPELLANT ROCKET ENGINE COMBUSTION CHAMBER MIXING HEAD

LIQUID PROPELLANT ROCKET ENGINE COMBUSTION CHAMBER MIXING HEAD

FIELD: heavy thrust rocket engines. SUBSTANCE: combustion chamber mixing head has equalizing mixing space connected with spaces of cooling unit of injector face, generator gas supply unit and combustion chamber. Channels are made over perimeter of injector face opposite to peripheral nozzles on sect...

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Bibliographische Detailangaben
Hauptverfasser: GOROKHOV V.D, MIKHAJLOV A.M, SKUFINSKIJ A.I, TATARKO A.I, CHERNICHENKO V.V, KHRISANFOV S.P, RUBINSKIJ V.R
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:FIELD: heavy thrust rocket engines. SUBSTANCE: combustion chamber mixing head has equalizing mixing space connected with spaces of cooling unit of injector face, generator gas supply unit and combustion chamber. Channels are made over perimeter of injector face opposite to peripheral nozzles on section whose width does not exceeds diameter of oxidizer nozzle passage area. These channels connect combustion chamber space with injector face cooling unit space. Optimum operating conditions of mixing head are provided when area of channels located at each peripheral nozzle is 0.15-0.2 of area of passage of oxidizer nozzle (for instance, oxygen nozzle). EFFECT: increased economy of operation of combustion chamber, increased thrust specific pulse. 2 cl, 5 dwg