Blade for a gas turbine engine

Details Blade for a gas turbine engine Blade for a gas turbine engine

2011-07-05

2011-07-05

Nguyen, Ninh H (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Laminated, embedded member or encased material

C416S24100B, C416S243000, C416S248000, C029S889720

Reexamination Certificate

active

07972116

ABSTRACT:
A blade for a gas turbine engine includes an aerofoil portion and a root portion defined by concave and convex walls having opposing inner surfaces. A reinforcing member is located between the concave and convex walls and is bonded to the inner surfaces of the concave and convex walls, and the root portion includes an unbonded region in which the reinforcing member contacts an inner surface of one of the concave and convex walls but is not bonded to the concave and convex walls.

REFERENCES:
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patent: 2004/0118903 (2004-06-01), Richardson et al.
patent: 2004/0253115 (2004-12-01), Williams et al.
patent: 1 013 883 (2002-01-01), None
patent: 0 719 079 (1954-11-01), None
patent: 2 399 866 (2004-09-01), None

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