METHOD OF OPERATION OF LIQUID-PROPELLANT ROCKET ENGINE WITH TURBOPUMP DELIVERY OF CRYOGENIC PROPELLANT ON BASIS OF FUEL AND OXYGEN OXIDIZER AND LIQUID-PROPELLANT ROCKET ENGINE FOR IMPLEMENTING SAID METHOD

FIELD: rocketry. SUBSTANCE: according to proposed method of operation of liquidpropellant rocket engine with turbopump delivery of cryogenic propellant on basis of oxygen oxidizer and fuel, recovering gas, after generation of vapor, is used directly for afterburning in chamber with remaining part of...

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Bibliographische Detailangaben
Hauptverfasser:	MIROSHKIN V.V, PRISHCHEPA V.I, BAKHMUTOV A.A, BUKANOV V.T, ROMASENKO T.JA, KLEPIKOV I.A
Format:	Patent
Sprache:	eng ; rus
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: rocketry. SUBSTANCE: according to proposed method of operation of liquidpropellant rocket engine with turbopump delivery of cryogenic propellant on basis of oxygen oxidizer and fuel, recovering gas, after generation of vapor, is used directly for afterburning in chamber with remaining part of fuel. Liquid propellant rocket engine implementing proposed method employs gas generator designed for generating recovering gas being connected directly to nozzle head of chamber. EFFECT: increased efficiency of liquid-propellant rocket engine by increasing specific thrust pulse. 5 cl, 3 dwg