Patent ID: 7284957

Claim:
An integrally bladed rotor for use in a gas turbine engine comprising: a plurality of pairs of airfoil blades; each pair of blades having a spar which extends from a first end tip at an outer end of a first one of said airfoil blades in said pair to a diametrically opposed second end tip at an outer end of a second one of said airfoil blades in said pair; said spar in a central region having a first arm and a second arm, said second arm being positioned on top of said first arm and being spaced from said first arm so as to define an opening with said first arm which allows the spars of said plurality of airfoil blades to be interwoven; and said spar being formed from an organic matrix composite material having continuous reinforcing fibers running through a center in tension with a majority of said reinforcing fibers generally axially aligned with a longitudinal axis of the spar.