Well, I am pleased to report that my turbo, stock housing with TO4
 wheel and 60-1 compressor with a fixed open waste gate has lasted
 over 230 hrs without a single problem.  The solution to good enough?
 Make it better.  I just finished my annual during which I upgraded
 my turbo to a similar TO4 big shaft wheel, but now it has a TO4E 50-
 trim compressor and the wastegate flapper and actuator are back in
 place.  Why the change?  Either I am a glutton for punishment or I
 am starting to pin down this turbo issue.  For those of you not
 familiar with my turbo history, here is a quick recap:

 First turbo - the stock second generation with waste gate flapper
 installed, ridden hard and put away wet...  it was run at full
 throttle at high altitudes, often at peak EGT.  It lasted 70 hrs
 before the turbine wheel fell apart and broke off.  The thought at
 the time was that the stock turbo was just too small for this heavy
 duty abuse and was overspeeding at altitude.

 Second turbo - small shaft TO4 wheel with 60-1 compressor and
 removed waste gate flapper.  It was also run mostly at peak EGT but
 the power produced was somewhat lower because of the bypassed
 exhaust.  It lasted about 140 hrs until it suffered the same fate as
 the first turbo while I was in a long full power decent (read extra
 high RPM and EGT's).  My thinking at this point is that the high
 EGT's are primarily the problem.

 Third Turbo - The one I just removed after 230 hrs.  Same
 configuration as the second but I kept the EGT's under 1600, mostly
 as lean as I could while keeping the engine running not too rough.
 It was also run at pretty low pressure ratios.  It could only make
 about 38" MAP on take off and about 40" at full bore down lot.  At
 16k altitude it was down to about 22".  My curiosity now is weather
 I can perhaps increase the boost and continue to have the turbo last,
 as long as I keep the EGT's under 1600.  I know, glutton for punishment...

 Other issues..

 Lean of Peak operation.  During the turbo change I discovered that
 my stock cast iron exhaust manifold had developed a number of
 serious cracks and some advanced erosion.  Much of the
 erosion/oxidation was near the mating surface with the turbo and it
 had started a small leak.  My concern is that all those hours of LOP
 operation allows too much oxygen into the exhaust to promote to
 oxidation and accelerates the problem.  The question is, should I
 start running rich of peak to prevent rusting away the exhaust
 system components?  ROP operations also allow me to keep even lower
 EGT's (for the turbo) and smoother engine running (for the wife).
 Turbos and exhaust components that I get from cars usually have the
 appearance of being run rich, rather than the dry orange color of
 the inside of my components.  The only obvious downside is the
 obvious much increased fuel usage.  I think that for the next couple
 hundred hours I have going to have to bite the bullet and fly ROP
 (while at higher power settings).  Thoughts?

 S.A.G. is really baffling.  Spark plugs only seem to be lasting 20-
 30 hrs before SAG starts kicking in.  Noted by a distinct and marked
 loss of power as I cross through about 1500' AGL after take off.
 The problem is usually intermittent and mildish at first becoming
 more consistent and remarkable as the hours accumulate on the spark
 plugs.  The problem is always solved by changing out the spark
 plugs.  I am switching to colder platinum plugs in order to try to
 get them to last longer.  Perhaps running ROP will help them last
 long too?

 Time for a new Prop?  On a test flight yesterday, the engine was
 running great.  No SAG.  At 7000' and 33"MAP I was at 6500 RPM,
 about 1/3 throttle and doing 175 KTAS [201 MPH].  It is a 64
 length x 77 pitch 3-blade Cato, but that is more like an
 effective pitch of closer to 71".  I seem to remember being able
 to get closer to 185 KTAS [213 MPH] at 6500 RPM in the past on
 the same prop but I did have a little taken off because of the
 low output of the previous turbo.  After some more experience I
 may discover that it is time for another new prop.  Might soon
 contact Paul Lipps, I liked his article in the last issue of
 Contact!  mag.  If that is my worst problem, I am going to be
 pretty happy.

 Doing some formation flying with the guys next week that may make
 its way into a movie...

 Keep building!
 --
 David Leonard

 Turbo Rotary RV-6 N4VY
 http://N4VY.RotaryRoster.net <http://n4vy.rotaryroster.net/ <
http://n4vy.rotaryroster.net/
 http://RotaryRoster.net <http://rotaryroster.net/ <
http://rotaryroster.net/

 I really appreciate Dave's persistence on exploring
 turbo charged rotaries in aircraft use.

 The turbo life issue is not only the EGT it is the turbo RPM as well.
 If the RPM is high enough the blades will disintegrate regardless
 of the turbine inlet temp. The load on the blades is M times V
 squared divided by R. V is the the tangential velocity of the blade
 CG. M is the mass of the blade. R is the radius of the blade CG. All
 rotating device suffer from this problem. As the temp goes up the
 strength of the blade material is reduced. At 1600 F strength of
 exhaust valve steel is down to 5000 psi which is next to nothing.
 See the attached chart. Epoxy resin is 3000 psi :)

 Here is a chart from Caterpillar on the situation. The turbine
 MUST be kept within the limit lines of both temperature AND rpm.

 I have repeatably tried to get Dave to install a Garret turbine
 RPM kit. In fact I will buy it and send it to him. No luck
 so far. If you send me the compressor Dave I will install
 the RPM sensor for you and send it back as well. Perhaps Zack can
 convince him :) We need to know the turbine RPM!!!!!

 Somebody needs to try a Capacitor Discharge ignition system
 to further investigate the spark plug "sag" problem.

 Inconel is probably the only answer to high temp corrosion
 of ferrous materials. I have seen many cracked cast iron
 turbo exhaust manifolds.

 Paul Lamar


 Hi Dave,
 Auto OEM "wisdom" dictates running rich while boosted to prevent
 detonation.
 Also autos are regularly being accelerated off lights etc, which will give
 the
 black soot.
 How would ceramic coating the turbine housing work to keep heat out of the
 metal? You would have to compensate for the thickness of the ceramic at
 the
 mating surfaces or have them masked off so you do not coat those areas.

 Dale Davies


 Dave,

 What is your new turbo make, number and trim?  Same as the Cozy
 Girls but with a built in waste gate?  I have a similar cast
 iron manifold as yours and you are welcome to have it.  That
 will get you in air fast.  A better long term solution would be
 if I  donate a custom fabricated exhaust manifold  to your
 cause.  I can with your dimensional assistance design and
 manufacture a stainless 316L with altered pipe ells, It would
 have a tangential junction connecting both runners so that an
 external  wastegate could divert the exhaust flow BEFORE it hit
 the turbine.   It will be more robust and lighter than the Mazda
 cast iron manifold you are now using.  Paul can attest to the
 quality of the welds at the shop near me.  Most of their works
 is  fabricating exotic alloys  and they can guarantee fitting by
 using my 13B assembled engine.

 In return I as well as others need flight data.  If you can fly
 to at least 18k,  and cruise rpms  near or over 6K engine rpm
 then the data you collect will be invaluable for not only my
 project but scores of turbo rotary want- to-be's.  Paul will
 lend you a turbo tach and I believe a few of us could cobble up
 a ten channel flight recorder so you don't have to take notes.

 What do you say?

 Doug in Japan.

 Now that is an offer you should not refuse Dave.
 Doug's shop is second to none.
 3/16th inch thick 316 SS plate is ten times better than cast iron.
 Here is a simple design that will divert the exhaust
 gas before it reaches the turbine. The is the ultimate waste
 gate. Zero to 100%. This 3D could be dimensionally interchangeably with
 the stock cast iron 1990 manifold Dave is using now. Same
 dimensions.

 Paul Lamar



HI Doug,
Wow, that is quite an offer and I am inclined to take you up on it if you
really want the data that badly, but I don't really need anything for the
time being (and IMHO, turbo tach data will not be particularly useful to
you
either).  But first to answer your questions.

I am using the stock series 5 housing and That is the ONLY thing that will
fit.  Really, I have tried everything.  My clearances are very tight and
changing one little thing cause a ripple effect that could keep me grounded
for a year or more.  Simply nothing else will fit.  Not even Pauls manifold
and wastegate above - the exhaust pipe from it would pass through my
radiator...

So given that I am stuck with the stock series 5 manifold and housing, it
is
ported larger to fit a big shaft turbine with and aggressive trim (not sure
which one)  Compressor and housing can be changed out to almost any of the
TO4 compressors.  I had some nice pictures showing my mods to the turbo,
but
just accidentally deleted them trying to move them to my computer.

Anyway, the manifold cracks are not a big deal.  I had a couple of spare
ones sitting around for just this occasion, and it could still probably be
used for many more hours.  Though someday I may change it out for a SS
manifold of the exact same dimensions.  In fact, if you think your shop
could make me an essential copy of the stock series 5 turbo exhaust
manifold
(89-91) then I would be glad to install Pauls turbo tach and get you all
the
data you want.  But I think it needs to be smooth flow, not a box type.
 Box
is likely to cause unacceptable back pressure.  Internal pipes would
probably need to be supported by some sort of box, as the turbo has no
other
support.  No need for a wastegate, as there is no place for me to send the
exhaust.  I am stuck using the stock (but ported) internal wastegate.

That is a pretty big and difficult project (would cost me a pretty penny
for
such a custom manifold) and I don't think it is worth your while. Let me
explain.  We have turbo maps that give us a very good approximation of the
turbo speed for given conditions.  Paul argues that there are too many
unknown factors in the mass flow so the maps are not that accurate.  Ok
fine.  But suppose the map predicts that the turbo is turning 90k RPM and
the tach shows it turning 100k. (the difference is unlikely to be
particularly large)  What now? We don't really know where we should be
drawing the line for continuous operation because it is a gray area trade
off between performance and durability.  Maybe you could fine tune your
compressor selection a little, but I am already running the biggest
(slowest
turning) compressor that matches the mass flow that I can find.  There are
bigger compressors, but they require much higher mass flows.

And if we do collect data, it really tells us more about the unknowns of my
system (like volumectric efficiency and intercooler pressure drop. etc)
than
helping you design your system.  And those unknowns are going to change
between particular installations.

None the less, if you are still interested, I would love to have a nice
custom SS manifold and as soon as it is done will fly up and "let" Paul
help
me install the turbo tach and come along to collect data if he wants. (or I
can do it myself, it is not hard to collect data).  One thing, since I cant
really run WOT with this turbo anywhere close to the ground (if at all) (it
would over boost the engine), we really need to also measure the pressure
upstream of the throttle body which will require the borrowing and
installing of a manifold pressure sensor as well. (not a huge issue)

--
David Leonard

Turbo Rotary RV-6 N4VY
http://N4VY.RotaryRoster.net <http://n4vy.rotaryroster.net/ <
http://n4vy.rotaryroster.net/
http://RotaryRoster.net <http://rotaryroster.net/ <
http://rotaryroster.net/

The turbo tach is NOT about turbo performance.
The turbo tach is NOT about boost level.

IT IS ABOUT STRESS ON THE BLADES.

Stress = M X V squared over R.

R is one M is one. 90K RPM squared is 8,100K.
100K RPM squared is 10,000K RPM .

10,000 divided by 8,100 is 24% more stress on the blades!!!!!!!

Small increases in RPM makes a huge difference in stress!!!!!

The stock 91 manifold has the turbo located in a asymmetric
location and just about 4 inches from the face of the rotor
housings. The diameter of the exhaust ports is 2 inches ID.

Assume for the moment we used the tightest tubing bend
we can find. That would be a 304 stainless railing casting
From RB Wagner. The center line radius is 2 inches.
As you can see from this to-scale-3D it is just not practical.
What ever you build it will turn into a box like
chamber and that is the reason Mazda did it that
way. There is just no room for a streamlined turbo
manifold that fits the stock turbo position.

Perhaps it could be done with a SS casting but the pattern
alone would cost thousands and the length of the runners
would be drastically different.

Perhaps it could be NC machined in two pieces of billet SS
and welded together but that would also be rather expensive
and the runner length would still differ.

Paul Lamar

I understand that it is about stress on the blades, but what will you do
with the data we collect?  Will you use it to pick a different turbo (one
that will be less stressed), or will you use it to set operational limits?
In either case, what is the  RPM limit that we need to stay under.  Again,
it is going to be a trade-off between durability and performance.

I didn't expect Doug to be able/willing to make such a manifold.  Definitely
not worth it with the stock versions going for $10 on e-bay and lasting
500hrs.  When that supply dries up I can consider a box of possibly re-doing
my engine compartment altogether.

David Leonard

Turbo Rotary RV-6 N4VY
http://N4VY.RotaryRoster.net
http://RotaryRoster.net

I am learning along with you and others on this subject.
The turbocharged rotary is a new animal in aircraft use.
The EGT is anywhere from 200 to 300 F higher compared
to a piston engine as far as TIT is concerned. GE started
in the 1920's developing turbo's for aircraft piston engines
so by the time WW II came a long they had a good feel for
turbo RPM and turbine life design.

This knowledge will add to our quantitative experience. We are
a long way from setting a red line RPM.  We should have been doing
this years ago. Perhaps by now we could have a RPM red line number.
We need to start gathering data some time. The scientific method
is to gather data first and then formulate a theory to
predict what will happen when similar circumstances arrive.
I know you know all that.

Perhaps it would have saved you and others the expenses of
replacing the turbo's. I am thinking of Mistral as well.
To my knowledge Dave Garber, back in 1973, was the first
to use a turbo charged rotary in an aircraft. Unfortunately he
had no interest in cruising at high altitude so we learned
little from that effort.

I suspect we can get a longer life out of a larger turbine
wheel running at lower RPM and then choosing a compressor
to provide the desired boost. It takes X amount of HP
to compress gas. That can be done with a larger turbine
wheel as torque goes up while RPM goes down. HP can remain
the same.  A larger, higher mass turbine, will run at a lower
temperature with a given mass flow at a given temperature.
We know that from disk brake experience.
That is probably a linear relationship. The RPM however
is a square law relationship so it is far more important
for blade life.

The down side is increased weight for the turbo but I think
that is a small price to pay for the potential increased
reliability.

Paul Lamar