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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 ...
The Russian RD-180 engine also employs a staged-combustion rocket engine cycle. Lockheed Martin began purchasing the RD-180 in circa 2000 for the Atlas III and later, the V , rockets. The purchase contract was subsequently taken over by United Launch Alliance (ULA—the Boeing/Lockheed-Martin joint venture) after 2006, and ULA continues to fly ...
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 .
The Vulcain is a gas-generator cycle rocket engine fed with cryogenic liquid oxygen and liquid hydrogen. It features regenerative cooling through a tube wall design, and the Vulcain 2 introduced a particular film cooling for the lower part of the nozzle, where exhaust gas from the turbine is re-injected in the engine. [14]
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"
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 to power electric generators and hydraulic pumps. Another common use of the term is in the industrial gases industry, where gas generators are used to produce gaseous chemicals
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 propellants were then fed into the gas generator for mixing and thrust chamber for burning. The engine uses a gas generator cycle to drive the turbo-pump turbine, which then exhausts this small amount of spent fuel. This is the identical cycle used with the Saturn rockets, but much less complex than the Space Shuttle engine system.
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