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Post by racket on Apr 1, 2023 17:11:35 GMT -5
Looks like a C30 first stage , is the wheel 6.37 inch dia , area at 5.86 sq ins is right
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WilliamTQ
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Joined: March 2015
Posts: 38 
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Post by WilliamTQ on Apr 2, 2023 1:01:28 GMT -5
Looks like a C30 first stage , is the wheel 6.37 inch dia , area at 5.86 sq ins is righ  dimensions matches what you said |
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Post by racket on Apr 2, 2023 1:33:17 GMT -5
There should be an area marked on the NGV stator
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WilliamTQ
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Joined: March 2015
Posts: 38
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Post by WilliamTQ on Apr 2, 2023 3:20:10 GMT -5
There should be an area marked on the NGV stator  yes Racket it’s marked AREA 5.86 the turbine blade   |
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WilliamTQ
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Joined: March 2015
Posts: 38
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Post by WilliamTQ on Apr 2, 2023 15:17:39 GMT -5
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Post by racket on Apr 2, 2023 16:32:50 GMT -5
nice big wheel , but you'd better get the compressor sorted before worrying about the turb end
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WilliamTQ
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Joined: March 2015
Posts: 38
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Post by WilliamTQ on Apr 2, 2023 17:10:21 GMT -5
nice big wheel , but you'd better get the compressor sorted before worrying about the turb end What’s your opinion on the compressor wheel is not suitable for what I’m trying to do? Would 100mm turbocharger compressor wheel be more suitable than 110mm? sorry I really like know the advantages and disadvantages between turbocharger style compressor wheel and the Honeywell 110mm wheel, if don’t mind me asking I’ve been trying to research the difference |
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Post by finiteparts on Apr 2, 2023 19:52:14 GMT -5
The compressor wheel that you have is different than the GTCP85 second stage compressor wheel that I have (it has similar p/n), in that mine has a portion of the shaft and the curvic coupling. But Garrett Airesearch made a ton of different varaints. So I can only assume that they are close in size. I actually have one of those turbine wheels and as you can see from the photos, they are close in sizing, but unfortunately have the opposite rotations.   As a way to estimate how much airflow you will be needing to make that level of thrust, I did a contour plot in GasTurb to show where you can expect to be if you have around a compressor efficiency of 80%, a turbine efficiency of 75%, 5% total pressure loss through the combustor and a turbine inlet temperature of 1650F.  As for the Garrett compressor. I can't find specifics on it, but just looking at the ratios, it is a low pressure impeller. You may be able to regrind the profile to get a more favorable tip height, but it is probably not good for a single stage compressor on a turbojet. But, I have not done any calculations on it, so I can't say I was trying to find some free time to work through an example, but I am just too busy these days. I will try to get something cobbled up to illustrate the calculations, but I cannot promise a time when I will complete them. Good luck, Chris |
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Post by finiteparts on Apr 2, 2023 21:15:31 GMT -5
FYI, to get a rough approximation of the the size of an impeller that can get you 3.0 lbm/s, you can assume a inlet face Mach number of 0.6, which is a relatively good rule of thumb for most turbochargers out there.
For a standard day:
Tt = 59 F
Pt =14.696 psia
then the required flow area is:
Area = 10.5 in^2
Diameter = 3.656 inches (92.9 mm)
The inducer diameter of the Honeywell wheel is nearly 4.5 inches and thus is way too big for your 80 kg (176.4 lbf) engine. You need something like a GT55 turbo to get the flow needed.
If the Honeywell impeller was run to a similar inlet face Mach number, it would be flowing roughly 4.55 lbm/s.
- Chris
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WilliamTQ
Member
Joined: March 2015
Posts: 38
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Post by WilliamTQ on Apr 3, 2023 5:19:21 GMT -5
FYI, to get a rough approximation of the the size of an impeller that can get you 3.0 lbm/s, you can assume a inlet face Mach number of 0.6, which is a relatively good rule of thumb for most turbochargers out there. For a standard day: Tt = 59 F Pt =14.696 psia then the required flow area is: Area = 10.5 in^2 Diameter = 3.656 inches (92.9 mm) The inducer diameter of the Honeywell wheel is nearly 4.5 inches and thus is way too big for your 80 kg (176.4 lbf) engine. You need something like a GT55 turbo to get the flow needed. If the Honeywell impeller was run to a similar inlet face Mach number, it would be flowing roughly 4.55 lbm/s. - Chris Perfect these are the kind calculations I need to understand |
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