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US 12,601,266 B2Granted
Composite airfoil assembly for a turbine engine
AssigneeGeneral Electric Company
InventorsNicholas Joseph Kray, Tod Winton Davis, Elzbieta Kryj-Kos, Michael John Franks
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Abstract
A composite airfoil assembly for a gas turbine engine, the composite airfoil assembly comprising a composite airfoil, a first cladding, and a second cladding. The composite airfoil having a core comprising a composite structure having a core bulk modulus and a laminate skin applied to at least a portion of an exterior of the core. The first cladding and the second cladding are coupled to an outer surface of the composite airfoil.
Claims11
A composite airfoil assembly for a gas turbine engine, the composite airfoil assembly comprising:
- a composite airfoil comprising:
- opposite pressure and suction sides extending radially from a root to a tip, the pressure side and the suction side defining an outer surface of the composite airfoil;
- opposite leading and trailing edges, the pressure side and the suction side extending axially between the leading edge and the trailing edge;
- a core comprising a composite structure having a core bulk modulus;
- and
- a laminate skin applied to at least a portion of an exterior of the core;
- at least three cladding elements including a first cladding element adjacent to the trailing edge and only located on the pressure side of the composite airfoil, a second cladding element adjacent to the trailing edge and only located on the suction side of the composite airfoil, and a third cladding element adjacent to the tip;
- and
- a leading-edge sheath located at the leading edge of the composite airfoil;
- wherein no portion of each of the first cladding element and the second cladding element are in contact with the trailing edge, and wherein no portion of the third cladding element is in contact with the tip, and wherein the at least three cladding elements comprise a metallic material.
7 more elements
A gas turbine engine comprising:
- a fan section, a compressor section, a combustor section, and a turbine section in serial flow arrangement, and defining an engine centerline;
- and
- a composite airfoil assembly rotatable about the engine centerline, the composite airfoil assembly comprising:
- a composite airfoil comprising:
- opposite pressure and suction sides extending radially from a root to a tip, the pressure side and the suction side defining an outer surface of the composite airfoil;
- opposite leading and trailing edges, the pressure side and the suction side extending axially between the leading and trailing edges;
- a core comprising a composite structure having a core bulk modulus;
- and
- a laminate skin applied to at least a portion of an exterior of the core;
- and
- at least three cladding elements including a first cladding element adjacent to the trailing edge and only located on the pressure side, a second cladding element adjacent to the trailing edge and only located on the suction side of the composite airfoil, and a third cladding element adjacent to the tip;
- and
- a leading-edge sheath located at the leading edge of the composite airfoil;
- wherein no portion of each of the first cladding element and the second cladding element are in contact with the trailing edge, and wherein no portion of the third cladding element is in contact with the tip, and wherein the at least three cladding elements comprise a metallic material.
11 more elements
Dependencies are inferred from the claim text.