aukap
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Post by aukap on May 2, 2015 19:54:34 GMT -5
Hi John, Maybe that snout gives me more dilution time till the gases hit the turbine wheel....
Morover that will aid in the fitment of the turbocharger to the combustion chamber with four securing bolts near the four corners.
Aukap.
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aukap
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Posts: 14
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Post by aukap on May 2, 2015 9:17:11 GMT -5
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aukap
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Posts: 14
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Post by aukap on May 2, 2015 9:14:24 GMT -5
So lately i have designed the flametube according to jetspecs or actually a bit oversized but the hole area and number was solely according to jetspecs.
27 x 6 mm holes in primary zone 10 x 8 mm holes in secondary zone 11 x 12 mm holes in tertiary zone.
Flametube diameter 6 inches, 12 inches long ,then 6 inches long taper and almost 6 inches rectangular tube matching the turbine inlet size.
Aukap
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aukap
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Post by aukap on May 2, 2015 9:10:19 GMT -5
Hi Guys, Carrying forward fron the general jet and turbine discussion.I am a final year mechanical engineering student.
The following build thread is of a gas turbine project based on a 55/83 compressor and 70/58 turbocharger. The build will be sort of "heavy duty?" since i don't want any combustion problems due to less time i have for sorting out the problems later on.
Aukap
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aukap
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Post by aukap on May 2, 2015 9:04:43 GMT -5
So the project has officially started....starting a new build thread in DIY engines sub group.
Aukap.
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aukap
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Posts: 14
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Post by aukap on Apr 15, 2015 7:42:13 GMT -5
This video reminds me of the jackass jet engine video
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aukap
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Post by aukap on Mar 28, 2015 5:15:05 GMT -5
This combustor geometry has been successfully used by some fellow users in this forum as i have seen, and moreover the geometry is designed totally according to jetspecs, air inlet near the turbine end, NO TANGENTIAL FEED, smooth transition(as you can see) into the turbine.
The temperatures at the turbine inlet came out to be very high nearly 1500-1600 K whereas in real world they come(as with the fellow users) some 1000-1100K and in simulation it was showing quite an amount of flame burning after the tertiary zone.
The parameters i used were:-
ZONE BOUNDARY CONDITION
Compressor feed Mass inlet(mass flow 0.3 Kg/s, pressure 2 bar, temperature 98 degrees celsius)
Turbine inlet(combustor outlet) Pressure outlet(pressure 2 bar)
Fuel inlet Mass inlet( Stoichometric ratio x mass inlet)
Model used K-epsilon with energy equation.
Anyone seeing this post if knows anything about CFD then please share if i am doing wrong anywhere due to which my turbine inlet temperatures are coming so high.
Aukap
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aukap
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Posts: 14
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Post by aukap on Mar 28, 2015 5:00:34 GMT -5
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aukap
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Posts: 14
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Post by aukap on Mar 28, 2015 4:58:22 GMT -5
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aukap
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Post by aukap on Feb 1, 2015 7:47:01 GMT -5
so i went to my professor with the presentation on a turbo based engine and he asked me what exactly i wanted to do after fabricating the engine,what my goal was. I was wondering if the turbocharger based engine could be used with bio gas , but i was concerned about it reaching self sustainability considering a low fuel pressure unlike an LPG cylinder.
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aukap
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Post by aukap on Jan 20, 2015 3:49:57 GMT -5
So I have decided to base the project on the combustion chamber. My intention is to vary the hole pattern and hole size from an initial design. I require a little help on the hole sizes for the zones, I did check jet specs and although it gives you the total area of holes but the size of the holes is pretty much a decision one has to make, so what is a good start point
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aukap
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Post by aukap on Jan 13, 2015 4:58:48 GMT -5
I went through some stuff and apart from hole diameters one needs to put swirlers in order to get the "magic circles" ,how do you design the swirlers?
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aukap
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Post by aukap on Jan 10, 2015 2:25:44 GMT -5
i did a little reading myself and i found that a combustion chamber is something that has to be designed befitting the requirements . I read about the hole areas in the primary ,secondary and tertiary zone being in the ration of 3:2:5 and since ill have to document the project i was wondering about the theoretical background of this result.I did find some stuff online but i found it too complicated to understand . Any help on this will be of immense benefit. thank you
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aukap
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Post by aukap on Jan 9, 2015 2:50:03 GMT -5
Im a senior year student and having studied a little of gas turbines wished to do a project on this. I was studying combustors and any ideas on this will be appreciated
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