US 12,442,305 B2
Composite airfoil assembly for a turbine engine
Nicholas Joseph Kray, Mason, OH (US); Tod Winton Davis, Cincinnati, OH (US); and 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 Jun. 1, 2023, as Appl. No. 18/327,172.
Prior Publication US 2024/0401482 A1, Dec. 5, 2024
Int. Cl. F01D 5/14 (2006.01)
CPC F01D 5/147 (2013.01) [F01D 5/141 (2013.01); F05D 2220/32 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A composite airfoil assembly for a turbine engine, the composite airfoil assembly comprising:
a composite airfoil having an outer surface defining a pressure side and an opposing suction side, with the pressure side and the suction side extending between a leading edge and a trailing edge to define a chord-wise direction and between a root and a tip to define a span-wise direction, the composite airfoil comprising:
a core comprising a composite structure; and
a laminate skin applied to at least a portion of an exterior of the core, wherein the laminate skin defines at least a portion of the outer surface of the composite airfoil;
a first cladding located at the trailing edge and a second cladding located at the tip, wherein the first cladding and the second cladding are coupled to the pressure side or the suction side and have adjacent segments; and wherein the first cladding extends toward the tip in the span-wise direction to a first end, the second cladding extends toward the root in the span-wise direction to a second end, and an interface is defined by a physical arrangement of the adjacent segments of the first cladding and the second cladding, wherein the interface is an overlapping interface or gap interface in the span-wise direction that extends from the first end and terminates at the second end.