Abstract: Gas turbine engines include fan, compressor, combustor, and turbine sections. An electric machine assembly includes a rotating component comprising a plurality of airfoils and a plurality of first electric machine elements, with each airfoil including a respective first magnetic material electric machine element. A housing is arranged radially outward from the airfoils and includes a circumferential slot. A second electric machine element is arranged within the circumferential slot in the form of a circumferential winding arranged radially outward from the rotating component. A control system is electrically connected to the second electric machine element. Rotation of the rotating component causes the first electric machine elements to generate a magnetic flux and induce a current within the second electric machine element and the control system is configured to distribute the induced current to at least one of a storage device or electrical components of the gas turbine engine.

Abstract: A stator assembly for an aircraft engine, has: vanes distributed about a central axis, a vane having: an airfoil extending from a first end to a second end along a span and from a leading edge to a trailing edge along a chord, the airfoil having a pressure side and a suction side opposed to the pressure side; a slot within the airfoil, the slot extending in a direction having a component along the chord, the slot located between the pressure side and the suction side; a port at the leading edge, the port fluidly communicating with the slot and with the gaspath; a mass located within the slot, the mass movable within the slot to shift a center of gravity of the vane in a chordwise direction; and a biasing member biasing the mass in a direction opposite a pressure force generated by the flow of fluid.