Talk:Gas-generator cycle

ISP and efficiency
This article seems to have conflicting information regarding ISP and efficiency:

"The gas generator turbine does not need to deal with the counter pressure of injecting the exhaust into the combustion chamber, this allows the turbine to produce more power and increase the pressure of the fuel and combustion chamber, thus increasing specific impulse or efficiency.

Ok, so the cycle allows for higher ISP.

"The main disadvantage is lost efficiency due to discarded propellant, though this efficiency loss can be outweighed in production engines by the higher chamber pressure's increase in net efficiency. Even so a gas generator cycle tends to have lower specific impulse than a Staged combustion cycle."

Ok, so it leads to lower ISP, except when it doesn't. Even so, it tends to.

I'm confused. Djd sd (talk) 00:35, 18 January 2009 (UTC)

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Could rearrange the Usage section
It would seem better to list the rocket launch systems on the same lines as the engines they use. Could even change to a 2 column table, or even add extra engine related columns eg for dates, thrusts ? Any objections ? - Rod57 (talk) 15:51, 21 April 2017 (UTC)

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