Sistema de vaporización mejorado para un lanzador espacial

Space launcher comprising a turbopump (30), a heat exchanger (40) and an exhaust nozzle (50) which are arranged in a fluid-flow exhaust duct (20), from upstream to downstream in a direction of fluid flow in said exhaust duct (20), the heat exchanger (40) being configured so as to carry out heat tran...

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Bibliographic Details
Main Authors DURI, Davide, BRANDELY, Anaïs, PENIN, Loïc
Format Patent
LanguageSpanish
Published 28.02.2024
Subjects
BLASTING
COMBUSTION ENGINES
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Summary:Space launcher comprising a turbopump (30), a heat exchanger (40) and an exhaust nozzle (50) which are arranged in a fluid-flow exhaust duct (20), from upstream to downstream in a direction of fluid flow in said exhaust duct (20), the heat exchanger (40) being configured so as to carry out heat transfer between a propellant circulating within the heat exchanger (40) and the fluid flowing in the exhaust duct (20), characterized in that it comprises a base (60) positioned in the exhaust duct (20) between the turbopump (30) and the heat exchanger (40), the base (60) being positioned in the centre of the fluid flow and comprising suction orifices formed in a wall of the base (60) that are configured so as to draw in a portion of a fluid flow around the base (60).
Bibliography:Application Number: ES20200737259T