Transpiration cooled blade for a gas turbine engine

Fluid reaction surfaces (i.e. – impellers) – With heating – cooling or thermal insulation means – Changing state mass within or fluid flow through working...

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Details

416225, 416241B, F01D 518

Patent

active

043147941

ABSTRACT:
A transpiration cooled blade for a gas turbine engine is assembled from a plurality of individual airfoil-shaped hollow ceramic washers stacked upon a ceramic platform which in turn is seated on a metal root portion. The airfoil portion so formed is enclosed by a metal cap covering the outermost washer. A metal tie tube is welded to the cap and extends radially inwardly through the hollow airfoil portion and through aligned apertures in the platform and root portion to terminate in a threaded end disposed in a cavity within the root portion housing a tension nut for engagement thereby. The tie tube is hollow and provides flow communication for a coolant fluid directed through the root portion and into the hollow airfoil through apertures in the tube. The ceramic washers are made porous to the coolant fluid to cool the blade via transpiration cooling.

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patent: 3846041 (1974-11-01), Albani
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patent: 4221539 (1980-09-01), Corrigan

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