Gas turbine for use in gas turbine engine i.e. turbo-engine, of aircraft, has guide tracks extending in axial direction with respect to axis, and blades moved along curved tracks by piston-cylinder that has front piston and rear piston

摘要

The turbine has a fan (12) arranged in an inlet area of the turbine and comprising a hub (29). Fan blades (30) are arranged at the hub, and guide tracks (31) are formed at outer circumference of the hub. The guide tracks extend in an axial direction with respect to an engine axis (1) and comprise a curvature, where blade roots (36) of the blades are supported at the guide tracks. The blades are moved along the curved guide paths by a piston-cylinder that has a front piston and a rear piston, where the pistons are supplied with hydraulic fluid by hydraulic channels.