US 11,982,205 B1
Airfoil having a spar assembly for a turbine engine
Nitesh Jain, Bangalore (IN); Abhijeet Jayshingrao Yadav, Bangalore (IN); Balaraju Suresh, Bangalore (IN); and Nicholas Joseph Kray, Mason, OH (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed on Feb. 20, 2023, as Appl. No. 18/171,490.
Claims priority of application No. 202211076366 (IN), filed on Dec. 28, 2022.
Int. Cl. F01D 5/14 (2006.01); F01D 5/28 (2006.01); F01D 9/02 (2006.01); F01D 9/04 (2006.01); F01D 25/24 (2006.01)
CPC F01D 5/147 (2013.01) [F01D 5/282 (2013.01); F01D 9/02 (2013.01); F01D 9/04 (2013.01); F01D 9/041 (2013.01); F01D 9/042 (2013.01); F01D 25/243 (2013.01); F01D 25/246 (2013.01); F05D 2220/323 (2013.01); F05D 2300/603 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An airfoil for a turbine engine, the airfoil comprising:
a spar assembly comprising:
a composite spar extending from a spar base to a tip, defining a longitudinal direction;
a metallic hub having a first end and a second end, wherein a portion of the composite spar is received by a portion of the metallic hub defining an overlapping region between the spar base and the second end, wherein, at the overlapping region, at least a portion of a spar exterior surface is in contact with an interior surface of the metallic hub; and
a composite body circumscribing a portion of the overlapping region and in contact with an exterior surface of the metallic hub and at least a portion of the spar exterior surface, wherein the composite body defines ng a structural joint between the composite spar and the metallic hub.