Tip vortex control on a rotor blade for a gas turbine engine

摘要

A rotor blade (32) for a gas turbine engine includes an attachment (34) and an airfoil (36). The airfoil (36)has a stagger angle (¦), a base region (50), a transition region (52) and a tip regions (54). The stagger angle (¦) changes as the airfoil (36) extends between the attachment (34) and a tip (46). The base region (50) is disposed adjacent to the attachment (34). The transition region (52) is located between the base (50) and the tip (54) regions. A rate of the change of the stagger angle (¦) in the transition region (52) is greater than a rate of the change of the stagger angle (¦) in the base region (50). The rate of the change of the stagger angle (¦) in the transition region (52) is greater than a rate of change of the stagger angle in the tip region (54).