Editing J-2X (Engine)

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 from the J-2==
[[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]] are 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]]
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-The '''J-2X''' is a modern [[gas-generator 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 [[Pratt & Whitney Rocketdyne]].
+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 to the J-2==
+==Differences from the J-2==
 [[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. 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. -->
+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]] are 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==
+[[Category:rocket engines]]
-*[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: Articles]]
-[[Category:Rocket engines]]
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