| 摘要 |
<p>The aircraft gas turbine has a fan in the inlet flow area of the aircraft gas turbine, where the fan is rotatable around an engine axis. The fan has multiple fan blades (30). Each fan blade is placed on a hub (29) by a blade foot (31), where the hub is rotatable around the engine axis and movable in the flow direction front area. Each fan blade is placed on an adjustment disk (32) that is movable in flow direction rear area, displaceable axially towards engine axis and placed torque proof on the hub. The setting angle of the fan blades is changed by axial movement of the adjustment disk. The hub is connected with a guide recesses (33).</p> |
