US 12,420,909 B1
Airfoil assembly having a composite spar
Benjamin Thomas Van Oflen, Cincinnati, OH (US); Gary Willard Bryant, Jr., Loveland, OH (US); Tod Winton Davis, Cincinnati, OH (US); Li Zheng, Cohoes, NY (US); Tomas Muchenik, Cincinnati, OH (US); Daryl John Burford, Coleford (GB); and Pawel Pres, Cheltenham (GB)
Assigned to General Electric Company, Evendale, OH (US)
Filed by GENERAL ELECTRIC COMPANY, Evendale, OH (US)
Filed on Mar. 4, 2025, as Appl. No. 19/069,332.
Int. Cl. B64C 11/04 (2006.01); F01D 5/14 (2006.01); F01D 5/28 (2006.01); F04D 29/34 (2006.01); F04D 29/38 (2006.01)
CPC B64C 11/04 (2013.01) [F01D 5/147 (2013.01); F01D 5/282 (2013.01); F04D 29/34 (2013.01); F04D 29/388 (2013.01); F05D 2300/603 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An airfoil assembly for a turbine engine, the airfoil assembly comprising:
an airfoil body comprising an outer wall bounding an interior, the outer wall extending between a leading edge and a trailing edge in a chordwise direction, and between a root and a tip in a spanwise direction;
a composite spar having an interior spar portion located at the interior of the airfoil body and an exterior spar portion exterior of the airfoil body;
a sleeve having a sleeve outer surface and a sleeve inner surface, wherein at least part of the exterior spar portion of the composite spar is received at the sleeve inner surface, and wherein a top portion and a bottom portion extend from the sleeve outer surface to the sleeve inner surface, a sleeve length measured in the spanwise direction from the bottom portion to the top portion; and
a set of lobes extending from the composite spar received by a set of recesses at the sleeve inner surface, wherein the set of lobes include a lobe length measured in the spanwise direction from a first lobe end to a second lobe end, wherein the lobe length is 10% or more of the sleeve length.