>     Hi,
>      Finally, got the rotor in the mail. Thanks to Paul. (Is it RX8 rotor? > I
>     remember that You mentioned that pocket and faces are machined. On > this one
>     pockets a left as cast.)
>     I agree totally with what Paul and Rob are suggesting.
>     Next steps:
>     1) Disassemble it.
>     2) Cut in two halves.
>     3) Scan it.
>     4) Create a valid 3D model of standard Mazda rotor.
>     Here I will need help from Rob.
>     Rob, as I understand You've got
>      all the math to model the rotor faces. If I
>     remember correctly You're working with Pro/E. Is it possible that You > model
>     outer geometry (faces) and send me the file (native Pro/E or any > common -
>     Parasolid, Step or IGES). Modeling the faces out of scan data is not > the best
>     idea IMHO.
>
>     5) As Rob mentioned "Cast Ti has anywhere
>     from a 1/2 to a 1/3 less thermal conductivity versus cast irons. 40
>     percent less density, half the expansion rate, double to triple the
>     tensile strength but anywhere from equal to half the modulus of
>     elasticity. If i were just looking at it, without changing any
>     dimension(based on modulus vs. tensile) it would be about 40 percent > of
>     the weight of the rotor."
>
>     If I remember it right Mazda rotor is made out of ductile iron. Its > properties:
>     Elastic Modulus 120000 N/mm^2
>     Poissons Ratio 0.31 Shear Modulus 77000 N/mm^2
>     Thermal Expansion
>      Coefficient 1.1e-005 Density 0.0071 g/mm^3
>     Thermal Conductivity 75 W/m K
>     Specific Heat 450 J/kg K
>     Tensile Strength 861.695 N/mm^2
>     Yield Strength 551.485 N/mm^2
>
>
>     Now for the Ti cast rotor I'm planning to use VT20L which was designed > for
>     extended work at 500C.
>        Fe     C      Si       Mo    V    N       Al    Zr       O > H
>     <0.3   <0.1  <0.15    2     2.5 <0.05    6     2    <0.15
>     <0.012
>
>     Elastic modulus 123000 N/mm^2
>     Poisson's ratio 0.33 Shear modulus 46000 N/mm^2
>     Thermal expansion coefficient 9e-006 Mass density 0.00465 g/mm^3
>     Thermal conductivity 7.8 W/m K
>     Specific heat 500 J/kg K
>     Tensile strength 1160 N/mm^2
>     Compressive strength 1170 N/mm^2
>     Yield strength 1070 N/mm^2
>     Hardening factor (0.0-1.0; 0.0=isotropic; 1.0=kinematic) 8.5e-007 > N/mm^2
>
>     Advantages that we may have:
>     Strength =   134.6%
>     E modulus = ~ 100%
>     Density =  65.5%
>     Thermal
>      conductivity =  10.4%
>     Thermal expansion =  82%
>
>     More than that at high temperatures  mech. prop. advantages will be > higher.
>
>     Anyway as Bob mentioned we can  safely assume 30% weight reduction of > rotor
>     assembly. I agree with Rob that revving the engine 20000RPM may cause > all sorts
>     of problems. But revving the  3 rotor engine to 12 - 13,000 RPM sounds > realistic
>     to me.
>
>     Now, what's the current thinking about feasible price for a 7 - 6.5lb
>     Titanium rotor? We're not talking about mass production but high power
>     applications.
>
>     Thank You
>     Ted
>
> Ted,
>
> I don't like scanning either. What is inherently wrong with it is that
> it only lets you copy something without having the ability to modify it.
> Point clouds to surfaces is a useless tool unless you are trying to
> knock something off. Part of all or our endeavors should be to
> understand what we are doing so when we want to make a logical changes
> they can be done easily and effectively. I think a particular good
> product would be a lower compression ratio rotor for the RX-8 for
> instance which has almost nothing to do with copying the current rotor.
>
> I think a very good idea would to send a rotor to a material science
> center, maybe the one we had at University at Buffalo, to determine
> exactly what type of cast iron that Mazda uses in the RX-8 rotors.
> Especially to find out what the hardness levels are at the apex seal
> slots. Cast iron is such a variety metal that speculating as to what it
> is pointless. Just test it. This should be on the hot list to do. Other
> rotors don't really matter so much since the RX-8 rotors are of the
> highest apparent quality/engineering. If we don't have real data on what
> we are trying to improve then it will make it harder to make the
> replacement as good as it could be.
>
> I couldn't tell you what the cost would be for a Ti rotor. I am looking
> into it and will let you guys know when I find out. Read up on the post
> up to this point.
>
> I don't use pro-e but that is the program it looks like we will need to
> use in order to accurately model the rotor and housing. Once done in
> pro-e it can be imported into solidworks. That os fine with me for now
> since the primary function is to replicate what Mazda has done but in the
> long run I want to try different configurations so a better solution
> will have to be found. I hope to find a way to make a macro that will
> have this functionality.
>
> Example:
>
> http://www.profilesmagazine.com/p33/marsalek.html
>
> Rob Woods


  Rob,
I like your thinking. I have compared the RX7 and RX8 rotors. The weight
difference between the lightest RX7 which Ted has and the RX8 isn't all that
much. I believe the walls and internal structures are more uniform in the
RX8 casting and one important point is that the area surrounding the apex
seal is smaller ( read shorter in the length of depth) - as the apex seal is
shorter.

So from a practical point of view coping the RX7 rotor is safer, the
differences in wall thickness ( to the RX8) are negligible.

If I've read my mail correctly recently I believe Paul sent that rotor to
Ted, and  sent that particular one probably for these reasons.

I've cut up a rotor and it appeared to me to be cast steel rather than cast
iron - but it certainly wouldn't hurt to know what it is exactly. I had the
e-shaft tested for the same reasons.
George ( down under)

  Hi All,
 I'd like to say one/several things.
As Paul mentioned Russia is mother of Titanium (around 70% of Earth deposition) and we have vast technologies to work with it (Casting/machining/surface treatment). It will be significantly cheaper than any other part of the world. This may lead to commercially feasible titanium rotor. I have all imaginable CAD/CAM/CAE tools and I can hire top level expertise in this areas (Less expensive than US/Europe) where I have no experience/time to deal with.
How ever I have no possibility to do it on my own (financially).
If there is some interested parties willing to share the effort than we can discuss and make some kind of consortium and make this happen.

My email is nevaracing at mail dot ru

Thank You
Ted