Patent ID: 8469656

Claim:
An airfoil seal system for airfoils of a gas turbine engine, comprising: a seal base configured to be received within a channel of a rotational airfoil proximate to a platform extending from the airfoil, wherein the seal base is generally an arcuate segment and wherein the seal base is configured to extend a length at least substantially equal to a length along an intersection between a rotational airfoil and an adjacent stationary component; a plurality of seal strips generally aligned with each other and overlapping each other, wherein the plurality of seal strips are attached to the seal base and extend generally radially inward from the seal base a length sufficient to seal a gap between the platform of the rotational airfoil and the adjacent stationary component; wherein the plurality of seal strips are flexible such that the seal strips may be flexed during operation of the gas turbine engine thereby sealing the gap between the platform of the rotational airfoil and the adjacent stationary component.