I am involved in a project to visualise flow through turbine and compressor cascades in a cascade wind tunnel and compare the results with the computer simulations in FLUENT.

This as a question to experts in the field of Turbomachinery.

I have observed that to change the angle of attack, a turn table kind of arrangement is generally used which rotates the complete cascade about some fixed point. It involves an arrangement for moving the side walls. However, if each blade is individually rotated by same amount to change the angle of attack, its a simpler arrangement and doesn't requires side wall movement. Still it isn't used so often. Is it because of the change in axial chord or due to some other reason? Does the axial chord change affect considerably?

Also, I found the profile data for compressor blade but I couldn't get airfoil data for turbine blade. I want to know where I can get such data.

Its quite urgent. If someone is capable of helping, please give few minutes of yours.

Nikhil

I think it's usually changing the side wall to change the attack angle, because of it's easier to implemente than change the cascade stagger angle. And the axial chord influent the test? I'm not sure about this.

About the turbine cascade data, I think there are much more sources to get than compressor cascade. Just use the google or search on some academic papers. There are more.

good luck

EddyXu