Difference between revisions of "J-2X (Engine)"
Jump to navigation
Jump to search
(→Differences from the J-2: added schematic) |
m |
||
| Line 3: | Line 3: | ||
==Differences from the J-2== | ==Differences from 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]] | + | 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. |
[[Category:rocket engines]] | [[Category:rocket engines]] | ||
{{Stub}} | {{Stub}} | ||
Revision as of 14:40, 17 January 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 from 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.