Thread: Stagger Angles for Turbine Blades

I am trying to find the stagger angle of a turbine blade.

I have already calculated the values of both Beta1 and Beta2. But I am struggling with the values of Alpha.

I have the radius, the Mach number, the rotational speed and the air temperature as well as knowing the incoming flow is entirely axial. I have also worked out the value for U using U=omega*r where omega=(2*pi*N/60)*r

I have two different triangles with the values of Omega relative, V absolute and U. One has only a Alpha relative angle and the other has an Alpha absolute angle.

I am unsure how to proceed to get the correct values of Alpha in order to find the stagger angles.

Any help you can give would be greatly appreciated.

Thanks

This is a rather specialized topic. I'm not sure any of our current members has expertise on this. If you could give a reference to the relevant theory and formulas that you are referring to, someone may be able to help.

Here's a link that might help you.

http://www.google.com/url?sa=t&rct=j...p3Sn64BzbyhC6g