Patent ID: 7967571

Claim:
An airfoil for a gas turbine engine rotor comprising: a blade root, a blade tip, a blade leading edge extending from the blade root to the blade tip, a blade trailing edge from the blade root to the blade tip, pressure and suction sides extending radially from the blade root to the blade tip, a blade inner span region between the blade root and a blade first height location on the blade leading edge and a blade outer span region between the blade first height location and the blade tip; transverse blade airfoil sections stacked between the blade root and blade tip having maximum blade airfoil section thickness located at a distance from the blade leading edge such that the relative distance of the airfoil section maximum thickness from the blade leading edge varies in a substantially linear manner between about 10 percent span and about 90 percent span; the blade leading edge having a sweep angle profile such that the sweep angle increases from the blade root to the blade first height location at a first rate of change of sweep angle with respect to span height that is substantially constant and the sweep angle increases from the blade first height location to the blade tip at a second rate of change of sweep angle with respect to span height that is substantially constant.