Gas-generator cycle

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Gas-generator rocket cycle. Some of the fuel and oxidizer is burned separately to power the pumps and then discarded. Most gas-generator engines use the fuel for nozzle cooling.

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 may be used to cool the nozzle and combustion chamber (regenerative cooling). 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 any rocket combustion chamber and nozzle heat mitigation, the engine would fail catastrophically.[1]


Gas-generator combustion engines include the following:

Rocket launch systems that use gas generator combustion engines:

See also[edit]


  1. ^ "ch2-6". 
  2. ^ a b "Vulcain-2 Cryogenic Engine Passes First Test with New Nozzle Extension" (PDF). ESA. 
  3. ^ "SpaceX Merlin Engine". SpaceX. 
  4. ^ a b "Delta 4 Data Sheet". 
  5. ^ Joe Stangeland. "Turbopumps for Liquid Rocket Engines". 
  6. ^ "J-2X Engine". 
  7. ^ a b "F-1 Engine Fact Sheet" (PDF). 
  8. ^ "RD-107". Encyclopedia Astronautica. 
  9. ^ 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. 
  10. ^ "Falcon 9 Overview". Archived from the original on 2013-05-01. 
  11. ^ "Falcon Heavy Overview". 
  12. ^ "Advanced Rocket Engines" (PDF). Institute of Space Propulsion, German Aerospace Center (DLR). 

External links[edit]