Hi,

I am working on cryogenic combustion of hydrogen for CUS rocket engines.
I have been trying this simulation since last 3 months but either i am not getting proper pressure rise in the chamber which should be around 60 bar or the velocity get too high.
Typical massflowrates for single element injector is
LOX : 200 g/s
GH2 : 34 g/s.
For H2-O2 engines minimum length required is
L* : 0.85 m.(it is characteristic length not length)

For signle element the following dimensions can be used
Throat Dia : 13mm
Contraction ratio : 2.5 to 4
Remaining dimensions can be estimate from the above data.

Sequence of operation are
T0 : H2 entry
T0+0.5 s : Igniter On
T0+0.7 s : LOX entry.

Injector geometry has been attached

If someone can help me out that will be really great.

Thanks

Regards,
Rajshekhar

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