turbine blades- design with no traditionally located stress peaks

[Apsu]

Does any one know of a method to design a gas turbine or compressor blade so that under a combined tension (CF) and gas bending load the traditional located stress peaks at LE,TE and Blade to Platform are avoided.

 

[rb1957]

simultaneous posting is not allowed ...

 

[johnhors]

You could try contacting Jura Carbon Limited (in the UK), I believe that they have developed such a blade design or something similar.

http://www.Roshaz.com