Wrt to the expander, seems likely to apply best to an open expander type where
you would burn the turbine drive for a little extra ISP
On Jul 13, 2016, at 5:54 AM, Ben Brockert <wikkit@xxxxxxxxx> wrote:
I was looking for the Aerojet Thrust Augmented Nozzle patent and ended
up finding a new patent application that was published this year. It's
written so broadly that it appears it would cover dumping any gas
generator cycle exhaust into the nozzle. Which is the standard thing
to do with GG exhaust, as demonstrated in the smoky F-1.
https://patents.google.com/patent/WO2016039993A1/en?q=thurst&q=augmented&q=nozzle&assignee=aerojet
Also claims the idea of running an expander cycle engine where the
propellant used to cool a first thrust chamber is burned in a second
chamber. Which means you could run the expander cycle at below first
chamber pressure, but you'd still have to pump up the first chamber's
propellant. And cool the second chamber. A diagram of work and
pressures would be handy to see the upside.