Wow! 44psi seems very high to me. In tethered ground testing I could only get about 44"Hg. You do have me thinking about a Blow Off Valve. I didn't want to add the complexity of waste gates & BOVs but my recent experience was somewhat predicted on this forum in the past. A turbo corvair powered RV-3 just went up for sale on the Vansairforce site due to 3 deadstick landings in a row, caused by prop drive failure. The intrepid builder did not seem to have sought help from experienced builders & operators of the type. This forum does a good job in that regard. Sent from my iPhone
Scott,
I have the stock 3rd gen intercooler.
I also have a blow-off valve set at 44psi to avoid overboost.
Regards,
John
On 7/8/2013 11:23 AM, Scott Emery wrote:
Last night (from epay) I bought a manifold pressure gauge for
a twin Cessna. The two needles are labelled Front & Rear.
It's marked 10 to 50 inches of mercury absolute. I intend to use
it to read turbo boost before the throttle body, and manifold
pressure after the throttle body.
I'm having a hard time finding an intercooler that fits the
available space plus has a usable configuration of inlet/outlet
tubes. The stock rx7 intercooler I have in hand seems the best
so far, but it's a bit small compared to aftermarket offerings.
Sent from my iPhone
I'm thinking my "Blown Engine" experience might be
avoidable in the future if I add a large manifold pressure
gauge in plain sight, install a 1.30 A/R exhaust housing,
retard the timing, run 100 LL blue gas, and add an
intercooler.
In that order.
I got an engine hoist yesterday so now I can put the
repaired engine back on. Getting it off didn't require as
much precision...
After I get some experience, I'll try different grades of
mogas @ defined manifold pressure limits.
Sent from my iPhone
OK, so the more accurate conversion is
20psi=40.7 in Hg
so in your example
20psi boost = 70.6 in MAP (Manifold Absolute
Pressure)
It help in your article, turbos work as a boost
ratio. So this turbo it then making a boost ratio of:
70.6 / 29.9 = 2.36
So as you go up in altitude you multiply the
ambient pressure by 2.36
So at 17,500 ft the pressure is half, and so is the
MAP, or, 35.3 " MAP
Losses are not porportunately reduced, and the
turbo may be less efficient in that range so actual
MAP may be less.
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