US 11,920,493 B2
Airfoil having a structural cell and method of forming
Douglas Lorrimer Armstrong, Needham, MA (US); Devin R. Dilley, Evendale, OH (US); and Elzbieta Kryj-Kos, Evendale, OH (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed on Feb. 25, 2022, as Appl. No. 17/681,162.
Prior Publication US 2023/0272718 A1, Aug. 31, 2023
Int. Cl. F01D 5/14 (2006.01)
CPC F01D 5/147 (2013.01) [F05D 2220/30 (2013.01); F05D 2230/50 (2013.01); F05D 2300/601 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A turbine engine, comprising:
a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement; and
an airfoil provided within at least one of the fan section, the compressor section, or the turbine section, the airfoil comprising:
an outer wall extending between a leading edge to a trailing edge to define a chord-wise direction, and between a root and a tip to define a span-wise direction, the outer wall defining an interior, a pressure side, a suction side, and a camber line extending through the interior between the leading edge and the trailing edge equidistant between the suction side and the pressure side, the interior extending a first distance along the camber line; and
a set of cells located within the interior, the set of cells extending a distance along the camber line a second distance, the second distance being less than the first distance, each cell of the set of cells having a shell comprising:
a forward portion and an aft portion provided aft of the forward portion with respect to the camber line, the forward and the aft portion being connected by side portions; and
a braided fabric having a first fiber extending along a first bias and a second fiber extending along a second bias, different from the first bias, provided along the forward portion, the aft portion, and the side portions.