US 12,031,453 B1
Component with spar assembly for a turbine engine
Nicholas Joseph Kray, Mason, OH (US); Nitesh Jain, Bangalore (IN); Abhijeet Jayshingrao Yadav, Bangalore (IN); and Balaraju Suresh, Bangalore (IN)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed on Feb. 1, 2023, as Appl. No. 18/104,452.
Claims priority of application No. 202211074559 (IN), filed on Dec. 22, 2022.
Int. Cl. F01D 5/14 (2006.01); F01D 5/28 (2006.01)
CPC F01D 5/147 (2013.01) [F01D 5/282 (2013.01); F05D 2220/323 (2013.01); F05D 2230/23 (2013.01); F05D 2250/75 (2013.01); F05D 2300/603 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A component for a turbine engine, the component comprising:
a wall bounding an interior and defining an exterior surface extending radially between a leading edge and a trailing edge to define a chordwise direction, and between a root and a tip to define a spanwise direction; and
a spar assembly comprising:
a metallic spar extending from a hub in the spanwise direction into the interior, the metallic spar defining a socket having at least one side opening;
a composite spar different than the metallic spar, the composite spar extending in the spanwise direction between a spar root and a spar tip, at least a portion of the spar root located in the socket; and
a stiffener bonded to at least one of the wall, the metallic spar, or the composite spar, at least a portion of the stiffener extending at least in part through the at least one side opening.