US 12,312,969 B2
Airfoils for turbofan engines
Trevor Howard Wood, Clifton Park, NY (US); Kishore Ramakrishnan, Rexford, NY (US); William Dwight Gerstler, Niskayuna, NY (US); Changjie Sun, Clifton Park, NY (US); and Lana Maria Osusky, Rexford, NY (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Jan. 17, 2023, as Appl. No. 18/155,118.
Prior Publication US 2024/0240571 A1, Jul. 18, 2024
Int. Cl. F01D 25/12 (2006.01); F01D 9/04 (2006.01); F01D 25/04 (2006.01)
CPC F01D 25/12 (2013.01) [F01D 9/041 (2013.01); F01D 25/04 (2013.01); F05D 2220/32 (2013.01); F05D 2240/12 (2013.01); F05D 2260/202 (2013.01); F05D 2260/96 (2013.01)] 19 Claims
OG exemplary drawing
 
1. An airfoil defining a spanwise direction, a chordwise direction, a root end, a tip end opposite the root end, a leading edge, and a trailing edge opposite the leading edge, the airfoil comprising:
a body extending along the spanwise direction between the root end and the tip end, the body comprising:
a plurality of acoustic cavities each having an inlet on the airfoil, the plurality of acoustic cavities extend into the airfoil generally parallel to a camber surface of the airfoil; and
at least one cooling channel having an inlet section, an outlet section and a middle section within the airfoil, the at least one cooling channel extending between the inlet section and the outlet section, wherein at least one inlet of the plurality of acoustic cavities is at the leading edge of the airfoil, wherein the body includes a cavity wall that extends into the airfoil generally parallel to the camber surface of the airfoil, and wherein the cavity wall defines at least one of the plurality of acoustic cavities; and
at least one porous face sheet positioned on at least one inlet of the plurality of acoustic cavities.