Turbo Jet Engine.
- Thread starter TurboWarrior
- Start date
I don't quite understand it either. Im sure someone on here does. I wonder how dangerous that actually is...
looked to be an open bucket of fuel ~1 foot from a red hot piece of steel. ide say its pretty safe:sarcasm:
foreverpsycotic said:
In the yellow fuel tank?
Looking at the video again I'm pretty sure the open container was oil.
turbo outlet goes into the exhaust side of the turbo compressed with fuel and is burned... (notice the loop and how hot it gets?)
turbo is to a jet engine what a wankle supercharger is to a rotary...
turbo is to a jet engine what a wankle supercharger is to a rotary...
Kind of interesting how they hooked up a second pump to the exhaust manifold for the afterburn effect.
Pretty cool idea but I bet longevity and efficiency go right out the window. Non the less, plus one for effort and ingenuity.
Pretty cool idea but I bet longevity and efficiency go right out the window. Non the less, plus one for effort and ingenuity.
Could modify a stock turbo, remove the center section and make a combustion chamber with fuel injectors to fit in there....After the turbine extend the end with a nozzle and have more injec tors to ignite the hot gases.
Damn....Wouldnt be very expensive to play with.
Cheers,
Roy
Damn....Wouldnt be very expensive to play with.
Cheers,
Roy
wouldn't work quite the same way, as the compressor isn't straight through...
basicly a jet engine is a linear compressor while you have to loop a turbo to do the same thing...
wonder how long the exhaust turbine lasts...
basicly a jet engine is a linear compressor while you have to loop a turbo to do the same thing...
wonder how long the exhaust turbine lasts...
Poodles said:
Oh yeah...true...I forgot the jet engine uses axial compressors unlike the automotive radial type compressors.
Cheers,
Roy
Early jet engines were centrifugal compressors very much like a turbocharger...
Not too different than the setup here. Just had a longer shaft between the compressor and turbine, the combustion chambers where located around the shaft..The axial flow become popular quickly cause it has a smaller frontal surface area=less drag...
OK, thats as geeky as I get LOL........
Not too different than the setup here. Just had a longer shaft between the compressor and turbine, the combustion chambers where located around the shaft..The axial flow become popular quickly cause it has a smaller frontal surface area=less drag...
OK, thats as geeky as I get LOL........