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Orbitec corporation has built an interesting rocket where oxydizer is tangentially injected in the chamber, forming a vortex insulating the wall. Fuel is injected centrally in the middle of the vortex, keeping the combustion far from the chamber wall.
http://www.gizmag.com/orbitec-vortex-li … ine/24807/
Orbitec is also developing a stoichiometric LOX-LH2 engine (F/O ratio =8) using vortex injection to protect the chamber form higher combustion temperature
http://www.orbitec.com/documents/SCORE_2006.pdf
A stoichiometric LOX-LH2 rocket may be very interesting for the possibility to use water propellant depot to be hydrolyzed before use.
Orbitec is also developing an interesting microwave electric thruster using water as propellant that can be used with the stoichiometric rocket: using the rocket to leave Earth orbit and the electric thruster to shorten the trip
http://aspw.jpl.nasa.gov/files/ASPW2014 … enburg.pdf
Last edited by Quaoar (2016-02-22 15:48:50)
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Here is a table of engine with fuel type to ratio that they are set to....
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Interesting idea to help with chamber cooling by tangential oxidizer injection. I would expect to see a mixing-rate penalty due to this injection geometry, leading to a longer chamber before nozzle entry. Maybe not a very big effect.
GW
GW Johnson
McGregor, Texas
"There is nothing as expensive as a dead crew, especially one dead from a bad management decision"
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The water fuel idea is about low thrust gaseous fuels to the vortex chamber and water to the microwave thursters....The first pdf document indicates that the throat and chamber lentghs do change the temperatures but that also depends of the ISP that is being produced according to the graph....
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