Difference between revisions of "J-2X (Engine)"
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| − | The '''J-2X''' is a modern [[ | + | The '''J-2X''' is a modern [[expander cycle]], [[bi-propellant]] [[rocket engine]], planned for use in the [[Ares I]] and [[Ares V]] [[launch vehicles]]. It consumes [[liquid hydrogen]] and [[liquid oxygen]]. It has its origin in the [[J-2 (Engine)|J-2]] rocket engines used by the [[Saturn Ib]] and [[Saturn V]] launchers. It is produced by [[Rocketdyne]]. |
| − | ==Differences | + | ==Differences to the J-2== |
[[Image:J2X_schematic.gif|thumb|right|Schematic of the J-2X]] | [[Image:J2X_schematic.gif|thumb|right|Schematic of the J-2X]] | ||
| − | While the J-2 was a [[gas-generator cycle]] or open cycle rocket engine, the '''J-2X''' uses so called [[tap-off cycle]] for powering its [[turbopumps]]. In such a cycle, a small part of the hot exhaust gases from the [[combustion chamber]] is used for powering the two turbopump assemblies. | + | While the J-2 was a [[gas-generator cycle]] or open cycle rocket engine, the '''J-2X''' uses so called [[tap-off cycle]] for powering its [[turbopumps]]. In such a cycle, a small part of the hot exhaust gases from the [[combustion chamber]] is used for powering the two turbopump assemblies. these turbopumps are connected in series with a hot-gas duct. After passing the oxidizer turbopump, the hot gases are directed into the nozzle exhaust stream. |
| + | ==References== | ||
| + | *[http://www.pw.utc.com/vgn-ext-templating/v/index.jsp?vgnextoid=2e35288d1c83c010VgnVCM1000000881000aRCRD&prid=e480c230314d3110VgnVCM100000c45a529f____ Pratt & Whitney Rocketdyne Awarded $1.2 Billion NASA Contract for J-2X Ares Rocket Engine] | ||
| + | *[http://astronautix.com/engines/j2s.htm J-2S on astronautix.com] | ||
| + | *[http://www.nasa.gov/pdf/187393main_j-2x_fact_sheet.pdf J-2X fact sheet from NASA (2.9 MB)] | ||
[[Category:rocket engines]] | [[Category:rocket engines]] | ||
{{Stub}} | {{Stub}} | ||
Revision as of 08:25, 5 November 2007
The J-2X is a modern expander cycle, bi-propellant rocket engine, planned for use in the Ares I and Ares V launch vehicles. It consumes liquid hydrogen and liquid oxygen. It has its origin in the J-2 rocket engines used by the Saturn Ib and Saturn V launchers. It is produced by Rocketdyne.
Differences to the J-2
While the J-2 was a gas-generator cycle or open cycle rocket engine, the J-2X uses so called tap-off cycle for powering its turbopumps. In such a cycle, a small part of the hot exhaust gases from the combustion chamber is used for powering the two turbopump assemblies. these turbopumps are connected in series with a hot-gas duct. After passing the oxidizer turbopump, the hot gases are directed into the nozzle exhaust stream.
References
- Pratt & Whitney Rocketdyne Awarded $1.2 Billion NASA Contract for J-2X Ares Rocket Engine
- J-2S on astronautix.com
- J-2X fact sheet from NASA (2.9 MB)