Patent ID: 6470670
Filing Date: 2002-10-29
Classification: F02K

Abstract:
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).