Patent ID: 8734101

Claim:
A gas turbine engine vane comprising: a composite airfoil having pressure and suction sides extending outwardly from an airfoil base to an airfoil tip, chordwise spaced apart leading and trailing edges of the composite airfoil at or near forward and aft ends of the vane, a single dovetail root extending chordwise from at or near the leading edge to at or near the trailing edge, the dovetail root connected to the airfoil base and slidably received in a chordwise extending dovetail slot in an inner vane mount for fixedly attaching the vane to a gas turbine engine frame, the dovetail slot having a triangular slot cross section and a flat slot bottom and flat slot pressure and suction side crush faces corresponding to pressure and suction sides of the airfoil and disposed at slot acute angles with respect to the flat slot bottom, the dovetail root having a triangular root cross section and a flat root bottom and flat dovetail root pressure and suction side crush faces corresponding to the pressure and suction sides of the airfoil and disposed at root acute angles with respect to the flat root bottom, and a biasing means for urging the root bottom of the dovetail root away from the slot bottom along the dovetail slot and pressing and preloading the flat dovetail root pressure and suction side crush faces of the dovetail root against the slot pressure and suction side slot crush faces.