Backswept turbojet blade
View Patent ↗A rotary turbojet blade comprises a plurality of blade sections extending along a line of the centers of gravity of said sections between a base and a tip, said blade presenting along a radial axis a bottom portion, an intermediate portion, and a top portion, said bottom portion presenting a longitudinal angle of inclination for a leading edge line, said intermediate portion presenting a backward longitudinal angle of inclination for said leading edge line, and said top portion presenting 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 in a direction opposite to the direction of rotation of said blade.
1. 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.
2. A blade according to claim 1 , wherein said bottom limit of the intermediate portion of the blade lies in the range 40% to 75% of the radial height of said blade between its base and its tip.
3. A blade according to claim 1 , wherein the longitudinal angle of inclination of the leading edge line of said bottom portion lies in the range −5° to 15° relative to said radial axis of the turbojet.
4. A blade according to claim 1 , wherein the backward longitudinal angle of inclination of the leading edge line of the intermediate portion lies in the range 5° to 20° relative to said radial axis of the turbojet.
5. A blade according to claim 1 , wherein the backward longitudinal angle of inclination of the leading edge line of said top portion lies in the range 20° to 50°, and the tangential angle of inclination of the line of the centers of gravity of the blade sections of said top portion lies in the range 20° to 50° relative to said radial axis of the turbojet.
6. A blade according to claim 1 , wherein said bottom portion further presents a tangential angle of inclination for the line of the centers of gravity of the blade sections lying in the range −5° to 15° relative to said radial axis of the turbojet.
7. A blade according to claim 1 , wherein said intermediate portion further presents a tangential angle of inclination for the line of the centers of gravity of the blade sections lying in the range −5° to 15° relative to said radial axis of the turbojet.