May 292010
From 1962… 6,000,000 pounds thrust, LOX/RP-1 propellants, 2000 psia chamber pressure, expansion ratio 14:1, Isp 283 sec at sea level, 304 sec vacuum. Sized for ease of transportation and manufacturing… which means it’s the small engine in the design study. More to come.
Note: the drawing came to me in B&W, like this:
But that’s boring, so I blueprintified it. Now it’s better.
7 Responses to “Rocketdyne L-6 booster engine”
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always wondered about that one when I’d see it mentioned in the Nova lineup.
You can see a lot of F-1 design extrapolation in the overall engine layout.
Considering all the trouble they had getting the F-1 and SSME to work properly, combining the two and scaling up the result to even larger size should have really kept them busy for a few years.
should have really kept them busy for a few years.
Shame it didn’t.
Jim
L-9H maybe? Any numbers bigger than 9?
> Any numbers bigger than 9?
Well, there’s the 30,000 K engine, with a diameter of 900 inches… but surely that must be *boring* so I won’t bother y’all with it…
Somewhat pedestrian, but please expound . . . . 🙂
Aerojet showed a 24M system at the 1964 Large Liquid Rocket Conference, but it had 12 or 24 thrust chambers in a common E-D nozzle so I don’t know if that counts as a single “engine”.
[…] to the L-6 previously described, but with hydrogen for fuel rather than RP-1. Chamber pressure, 1000 psia; 6,000,000 lbs thrust; […]