boeing767mech
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RB211-535E Combustion Question

Mon Jan 21, 2013 4:35 pm

So I have been doing boroscopes for a while and have noticed the higher time RB211-535E's have damage to the HPT (high pressure turbine blades) at the blade root trailing edge. Nothing to get excited about most of the time because it is within maintenance manual limits. But what is causing this damage on the roots when the noozle guide vanes in the combustion section have little or no damage????



HPT notice the dark area of the blade, (lower left corner of picture) this is the area of damage



Typical damage of high time engine of HPT

If anyone has any insight or knowledge of this I would be curious to understand the cause of damage to just this area and not the whole blade.

Thanks
David

[Edited 2013-01-21 08:35:54]
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HAWK21M
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RE: RB211-535E Combustion Question

Mon Jan 21, 2013 7:30 pm

Im curious why the root end "Trailing edge" not the "Leading edge".
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HAWK21M
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RE: RB211-535E Combustion Question

Tue Mar 26, 2013 7:50 pm

Anyone Aware......of the reason.
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ferpe
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RE: RB211-535E Combustion Question

Wed Mar 27, 2013 9:10 am

If you look up the CFD simulations there are on the net of the standard type turbine airfoils (2D) and the new ones designed with 3D CFD software you can see the standard ones have a highly vorticiced area at the roots. So the cause might be shedding of high energy local vortices which gradually erode the root area at the trailing edge, those dark eroded areas seems to be at the right place for that.

It shows why modern engines are more efficient, you get the transfer from gas energy to shaft hp to be more loss free.
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