Aircraft gas turbine with adjustable fan

摘要

The present invention relates to an aircraft gas turbine having a fan rotatable about an engine axis in the inflow region of the aircraft gas turbine, with the fan having several fan blades, with each fan blade being moveably mounted on a hub rotatable about the engine axis by means of its blade root on an area which is at the front in the flow direction, and with each fan blade being moveably mounted on an area at the rear in the flow direction, on an adjusting disk axially displaceable relative to the engine axis and non-rotatable with the hub, with the pitch angle of the fan blades being variable by the axial movement of the adjusting disk.

主权项

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.