Tip cambered swept blade
AssigneeGeneral Electric Company
InventorsAspi Rustom Wadia, Peter Nicholas Szucs, Max Robert Farson, Virginia Louise Wilson, William Joseph Solomon
Life of this patent
Estimating the term…
Abstract
A fan blade includes an airfoil having opposite pressure and suction sides extending in span between a root and tip, and extending in chord between opposite leading and trailing edges. From root toward tip, the airfoil includes increasing stagger and decreasing camber, and increasing chord length to barrel the airfoil along both the leading and trailing edges. The airfoil further includes forward aerodynamic sweep at the tip, and non-forward aerodynamic sweep between the maximum barrel and the root.
Claims23
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.
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 forward aerodynamic sweep at said tip, and non-forward aerodynamic sweep between a maximum barrel in said airfoil and said sloped root.
Dependencies are inferred from the claim text.