US 12,359,570 B2
Composite airfoil assembly for a turbine engine
Nitesh Jain, Bangalore (IN); Nicholas Joseph Kray, Mason, OH (US); and Abhijeet Jayshingrao Yadav, Bangalore (IN)
Assigned to General Electric Company, Evendale, OH (US)
Filed by GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed on Oct. 27, 2023, as Appl. No. 18/496,060.
Prior Publication US 2025/0137378 A1, May 1, 2025
Int. Cl. F01D 5/28 (2006.01); F01D 9/04 (2006.01)
CPC F01D 5/282 (2013.01) [F01D 9/041 (2013.01); F05D 2220/36 (2013.01); F05D 2300/6034 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A composite airfoil assembly for a turbine engine, the composite airfoil assembly comprising:
a composite airfoil extending between a leading edge and a trailing edge, the composite airfoil comprising:
an airfoil width measured from the leading edge to the trailing edge;
a woven core defining a core exterior, the woven core comprising:
a woven core thickness measured between a pressure surface and a suction surface of the woven core, wherein the woven core thickness is in a range from 5% to 30% of the airfoil width;
a first region comprising a first material having a first stiffness;
a second region comprising a second material having a second stiffness, with the second stiffness different from the first stiffness; and
a transition region coupling the first region and the second region, the transition region including the first material and the second material; and
a skin applied to at least a portion of the core exterior.