LIQUID-PROPELLANT ROCKET ENGINE WITH TURBOPUMP DELIVERY OF CRYOGENIC PROPELLANT

FIELD: rocketry. SUBSTANCE: proposed liquid-propellant rocket engine with turbopump delivery of cryogenic propellant includes chamber with nozzle head and cooled housed and turbopump set consisting of steam turbine and oxidizer, propellant and waste steam condensate pumps. Inlet of turbine is connec...

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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: proposed liquid-propellant rocket engine with turbopump delivery of cryogenic propellant includes chamber with nozzle head and cooled housed and turbopump set consisting of steam turbine and oxidizer, propellant and waste steam condensate pumps. Inlet of turbine is connected with condensate pump outlet through first main line including chamber cooling duct, and outlet of turbine communicates with condensate pump inlet through second main line with heat exchanger-condenser for cooling waste steam by cryogenic propellant component. Ejector with high-pressure nozzle connected to condensate pump outlet is arranged in second main line. EFFECT: reduced overall dimensions and mass of heat exchanger-condenser owing to decreasing its heat-exchange surface. 3 cl, 2 dwg