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The gas-generator cycle, also called open cycle, is one of the most commonly used power cycles in bipropellant liquid rocket engines. Propellant is burned in a gas generator (or "preburner") and the resulting hot gas is used to power the propellant pumps before being exhausted overboard and lost. Because of this loss, this type of engine is ...
This category is for those rocket engines using the pure gas generator cycle, like the Rocketdyne F-1, or the steam generator cycle, like the RD-107. Pages in category "Rocket engines using the gas-generator cycle"
Print/export Download as PDF; ... Rocket engines using the gas-generator cycle (79 P) P. ... Pages in category "Rocket engines by cycle"
Printable version; Page information; ... distribute and/or modify this document under the terms of the GNU Free Documentation License, ... Gas generator rocket cycle ...
The term often refers to a device that uses a rocket propellant to generate large quantities of gas. The gas is typically used to drive a turbine rather than to provide thrust as in a rocket engine. Gas generators of this type are used to power turbopumps in rocket engines, in a gas-generator cycle. It is also used by some auxiliary power units ...
The RD-119 (GRAU Index 8D710) was a liquid rocket engine, burning liquid oxygen and UDMH in the gas-generator cycle. [3] It has a huge expansion ratio on the nozzle and uses a unique propellant combination to achieve an extremely high isp of 352 s for a semi-cryogenic gas-generator engine. It also has a unique steering mechanism.
The engine uses a gas-generator cycle developed in the United States in the late 1950s and was used in the Saturn V rocket in the 1960s and early 1970s. Five F-1 engines were used in the S-IC first stage of each Saturn V, which served as the main launch vehicle of the Apollo program .
Engine cycle Liquid propellant rocket engine burning RG-1/LOX in a gas-generator cycle with the turbine driven by steam generated by catalytic decomposition of H 2 O 2: Nozzles Four main combustion chambers and two vernier thruster combustion chambers for attitude control Combustion chamber pressure 5.88 MPa (853 psi) 5.88 MPa (853 psi)