Cool! It's not often that people make these that can do more than just keep themselves running. Just curious about the numbers, have you measured the fuel flow and thrust with and without the afterburner?
Yes I have...The engine itself is reasonably efficient, at full noise the engine consumes ~2.75lbs of air/sec, (165lb/min), so at ~70,000rpm she'll consume approx 5.1Liters of fuel per minute. Actual static thrust is ~165lbs without A/B depending on ambient conditions.
The After-burner on the other hand is horribly inefficient...uses a ridiculous amount of fuel....but it makes ~30-35% extra thrust and all the right noises so I don't really care..

Static thrust with A/B is ~215lbs @20C and sea level conditions.
Heres some numbers and notes I made some time back...........
70,000 rpm 3.65 PR ( 35 psi P2) at 74% efficiency. With 2.75 lbs/sec - 165 lbs/minute flow.
175 deg C rise in compression stage, 190 C for T2 on a "cold??" winters day at 15 C.
~150 deg C drop through turb stage assuming 78% efficiency.
3% pressure drop across combustor, therefore a 3.54 PR going into turb stage at 900 C - 1173 K for calculations.
We need a 2.046 PR across turb stage to power the comp which should leave around a 1.73 PR or 10.7 psi total in the jetpipe.
I started to make some assumptions at this point to determine the actual PR across the turb stage to account for the velocity out of the turb exducer, I came up with a total PR of ~2.39 across the stage .
The official Garrett turbine stage map gives a Correct Flow of 93 lbs/min thru the 1.47 A/R scroll equipped stage.
Using a 1173K temp and a 3.54 PR along with the 93 lbs/min corrected flow, the actual flow worked out at 163 lbs, pretty close to our 165 lbs/min assumption of flow.
Our non A/B calcs .............1.73 PR @ 1023 K should give us a temp drop of ~117 deg C through a 90% effic jet nozzle at 906 K EGT and a velocity of 1720 ft/sec for a thrust of ~167 lbs.
Density will be ~41 cubic feet/ pound so ~112.75 CFS requiring ~9.44 sq ins of jet nozzle, or ~3.46 inch dia - 88mm, theoretically without any adjustment for boundary layer etc etc, I'd normally add on a couple of mm's, so 90mm would be reasonable .
Now for the A/B
If we apply the "normal?" ............double the CFS because of temperature rise, and divide by 1.4 for velocity increase ( square root 2 = 1.4 ), we get an area of ~13.5 sq ins, or 4.15 " dia, or ~105mm for the A/B nozzle, to allow for any "turbulence" and boundary layer a 110mm ID jet nozzle is required and thrust should be at ~215 lbs static.
Hope this helps.
Cheers,
Smithy.