Gas-generator cycle
The gas-generator cycle is a power cycle of a bipropellant rocket engine. Some of the propellant is burned in a gas generator and the resulting hot gas is used to power the engine's pumps. The gas is then exhausted. Because something is "thrown away" this type of engine is also known as open cycle.
There are several advantages to the gas-generator cycle over its counterpart, the staged combustion cycle. The gas generator turbine does not need to deal with the counter pressure of injecting the exhaust into the combustion chamber. This simplifies plumbing and turbine design, and results in a less expensive and lighter engine.
The main disadvantage is lost efficiency due to discarded propellant. Gas-generator cycles tend to have lower specific impulse than staged combustion cycles.
As in most cryogenic rocket engines, some of the fuel in a gas-generator cycle is used to cool the nozzle and combustion chamber. Available construction materials cannot withstand the extreme temperatures of rocket combustion processes by themselves, while cooling permits the use of rocket engines for relatively long burn times. Without rocket combustion chamber and nozzle heat mitigation, the engine would fail catastrophically.[1]
Usage
Gas-generator combustion engines include the following:
- Vulcain,[2] HM7B
- Merlin rocket engine[3]
- RS-68[4]
- RS-27A[5]
- J-2X[6]
- F-1 (rocket engine)[7]
- RD-107[8]
- CE-20[9]
Rocket launch systems that use gas generator combustion engines:
- Ariane 5[2]
- Falcon 9,[10] Falcon Heavy[11]
- Delta IV[4]
- Saturn V[7]
- Soyuz (rocket family)
- Geosynchronous Satellite Launch Vehicle III[9]
- Long March 3B, Long March 2F[12]
See also
References
- ^ "ch2-6". nasa.gov.
- ^ a b "Vulcain-2 Cryogenic Engine Passes First Test with New Nozzle Extension" (PDF). ESA.
- ^ "SpaceX Merlin Engine". SpaceX.
- ^ a b "Delta 4 Data Sheet".
- ^ Joe Stangeland. "Turbopumps for Liquid Rocket Engines".
- ^ "J-2X Engine".
- ^ a b "F-1 Engine Fact Sheet" (PDF).
- ^ "RD-107". Encyclopedia Astronautica.
- ^ a b Asraff, A and Muthukumar, R and Ramnathan, T and Balan, C (2008). Structural Analysis of Propulsion System Components of an Indigenous Cryogenic Rocket Engine. 44TH AIAA/ASME/SAE/ASEE JOINT PROPULSION CONFERENCE & EXHIBIT. doi:10.2514/6.2008-5120.
{{cite conference}}: CS1 maint: multiple names: authors list (link) - ^ "Falcon 9 Overview".
- ^ "Falcon Heavy Overview".
- ^ "Advanced Rocket Engines" (PDF). Institute of Space Propulsion, German Aerospace Center (DLR).
External links
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