Patent ID: 7108486

Claim:
A rotary turbojet blade that is to be subjected to a longitudinal gas flow, said blade comprising a plurality of blade sections extending along a line of the centers of gravity of said blade sections between a base and a tip of said blade, said blade being defined longitudinally between a leading edge and a trailing edge, said blade presenting along a radial axis of said turbojet a bottom portion, an intermediate portion, and a top portion, said bottom portion extending radially from said blade base to a bottom limit of said intermediate portion, and said top portion extending radially from a top limit of said intermediate portion to said blade tip, wherein said bottom portion presents a longitudinal angle of inclination for a leading edge line, said intermediate portion presents a backward longitudinal angle of inclination for said leading edge line, said top portion presents a backward longitudinal angle of inclination for said leading edge line and a tangential angle of inclination for said line of the centers of gravity of the blade sections in a direction opposite to the direction of rotation of said blade, and said top portion further comprises a top zone extending radially to said blade tip in which the leading edge line presents a forward longitudinal angle of inclination.