FAN STAGGER ANGLE FOR GEARED GAS TURBINE ENGINE

摘要

A gas turbine engine includes a spool, a turbine coupled with the spool, a propulsor coupled to be rotated about an axis by the turbine through the spool and a gear assembly coupled between the propulsor and the spool such that rotation of the spool results in rotation of the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. Each of the propulsor blades has a span between a root at the hub and a tip, and a chord between a leading edge and a trailing edge such that the chord forms a stagger angle alpha with the axis. The stagger angle alpha is less than 62° at all positions along the span, with said hub being at 0% of the span and the tip being at 100% of the span.