Liquid fuel rocket engine with a closed flow cycle
AssigneeAstrium GmbH
InventorChris Udo Maeding
Life of this patent
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Abstract
A liquid fuel rocket engine with a closed direct auxiliary flow cycle has a combustion chamber connected to each liquid fuel source through a respective main liquid fuel supply line. A turbo pump is provided in each main fuel supply line. The turbo pump is driven by a gas generator which is connected to a first bypass fuel supply line for supplying fuel to the gas generator. An exhaust gas duct (8, 9, 10) leads from the gas generator into at least one main fuel supply line for feeding gas generator exhaust gas into the main fuel supply line upstream of the turbo pump.
Claims9
A liquid fuel rocket engine with a closed direct flow cycle, said engine comprising a combustion chamber (14), at least one liquid fuel supply line (1) for supplying liquid fuel to said combustion chamber, an oxidizer supply line (2) for supplying liquid oxygen to said combustion chamber (14), at least one first turbo pump (3) in said liquid fuel supply line (1), at least one second turbo pump (4) in said oxidizer supply line (2), a gas generator (7), an auxiliary fuel line (5) connecting said gas generator (7) to said at least one liquid fuel supply line (1), an auxiliary oxidizer supply line (6) connecting said gas generator (7) to said at least one oxidizer supply line (2), an exhaust gas duct (8, 9, 10) connecting an exhaust gas flow of said gas generator (7) to said oxidizer supply line (2), wherein at least one portion (9) of said exhaust gas duct (8) is connected to said oxidizer supply line (2) upstream of said second turbo pump (4) as viewed in an oxidizer flow direction toward said combustion chamber (14).
Dependencies are inferred from the claim text.