| US 7,476,086 B2 | ||
| Tip cambered swept blade | ||
| Aspi Rustom Wadia, Loveland, Ohio (US); Peter Nicholas Szucs, West Chester, Ohio (US); Max Robert Farson, West Chester, Ohio (US); Virginia Louise Wilson, Walton, Ky. (US); and William Joseph Solomon, Cincinnati, Ohio (US) | ||
| Assigned to General Electric Company, Schenectady, N.Y. (US) | ||
| Filed on Aug. 22, 2005, as Appl. No. 11/209,085. | ||
| Application 11/209085 is a continuation in part of application No. 11/100752, filed on Apr. 07, 2005, granted, now 7,374,403. | ||
| Prior Publication US 2007/0243068 A1, Oct. 18, 2007 | ||
| Int. Cl. B64C 27/46 (2006.01) | ||
| U.S. Cl. 416—223R [416/242; 416/DIG. 5] | 23 Claims |
| 1. A gas turbine engine fan blade comprising:
an airfoil extending outwardly from a sloped root and including opposite pressure and suction sides extending longitudinally
in span from said root to an opposite tip, and extending axially in chord between opposite leading and trailing edges;
said airfoil further including stagger increasing between said root and tip, camber decreasing therebetween, and chord length
increasing outboard from said root to barrel said airfoil along both said leading and trailing edges; and
said airfoil includes maximum forward aerodynamic sweep at said tip transitioning to maximum aft sweep inwardly along said
leading edge in said barrel, and decreasing in aft magnitude to non-forward sweep at said root.
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