Patent ID: 9194397
Filing Date: 2015-11-24
Classification: F01D,F02K,F04D,F05D,Y02T

Abstract:
1. An aircraft gas turbine comprising: a fan rotatable about an engine axis in an inflow region of the aircraft gas turbine, the fan including: a hub rotatable about the engine axis; an adjusting disk rotational fixed with respect to the hub; one of he adjusting disk and the hub being axially displaceable relative to the other a plurality of fan blades, each fan blade including a blade root having a front area offset forward of a radial axis of the fan blade with respect to a flow direction through the fan and a rear area offset rearward of the radial axis of the fan blade with respect to the flow direction through the fan; each fan blade being moveably mounted at the front area to one of the hub and the adjusting disk and at the rear area to another of the hub and the adjusting disk, a pitch angle of the fan blades being variable by the axial displacement of the one of the adjusting disk and the hub relative to each other; wherein the axial displacement causes each fan blade to pivot around at least one chosen from the front area and the rear area, offset from the radial axis of the fan blade.