US 12,435,636 B1
Composite airfoil for a turbine engine
Gary Willard Bryant, Jr., Loveland, OH (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on May 23, 2024, as Appl. No. 18/672,367.
Int. Cl. F01D 5/28 (2006.01)
CPC F01D 5/282 (2013.01) [F05D 2300/603 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A composite airfoil for a turbine engine, the composite airfoil having an airfoil outer surface defining a pressure side and a suction side, opposing the pressure side, which extend between a leading edge and a trailing edge in a chordwise direction, and from a root to a tip in a radial direction, the composite airfoil comprising:
at least one airfoil body element comprising:
a plies core comprising a set of composite plies defining:
a pressure surface facing the pressure side; and
a suction surface facing the suction side, with the pressure surface and suction surface extending between a fore end, proximate the leading edge, and an aft end, proximate the trailing edge, and wherein the set of composite plies are contiguous between the pressure surface and the suction surface, and between the fore end and the aft end;
wherein at least the fore end, the aft end, and a tip end, proximate the tip, define a peripheral edge of the composite airfoil; and
a composite wrap overlying at least a portion of the plies core, wherein the composite wrap is in contact with and extends from the pressure surface, over the peripheral edge, and to the suction surface.