US 12,286,903 B2
Turbine engine including a composite airfoil assembly having a dovetail portion
Benjamin Thomas Van Oflen, Cincinnati, OH (US); Gary Willard Bryant, Jr., Loveland, OH (US); Michael John Franks, Cincinnati, OH (US); Elzbieta Kryj-Kos, Liberty Township, OH (US); Nicholas Joseph Kray, Mason, OH (US); and Arthur William Sibbach, Boxford, MA (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed on Feb. 24, 2023, as Appl. No. 18/173,989.
Prior Publication US 2024/0287911 A1, Aug. 29, 2024
Int. Cl. F01D 5/30 (2006.01); F01D 5/28 (2006.01)
CPC F01D 5/3007 (2013.01) [F01D 5/282 (2013.01); F05D 2220/32 (2013.01); F05D 2240/24 (2013.01); F05D 2240/30 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A turbine engine comprising:
a disk rotatable about a rotational axis and having:
a disk forward surface;
a disk aft surface;
a periphery interconnecting the disk forward surface and the disk aft surface; and
a slot extending axially along the periphery between the disk forward surface and the disk aft surface, the slot having an inner slot face radially opposite the periphery; and
a composite airfoil assembly comprising:
an airfoil portion extending radially outward from the periphery, the airfoil portion having opposing side walls extending between a root and a tip and between a leading edge and a trailing edge;
a dovetail portion extending from the root and being slidably received within the slot, the dovetail portion having:
a radially inner surface that extends axially, with respect to the rotational axis, a total axial length between the leading edge and the trailing edge, the radially inner surface spaced radially from the inner slot face to define a gap therebetween; and
a side wall, which meets the radially inner surface to define a dovetail corner;
a centerline extending from the radially inner surface to the tip, the centerline being equidistant between the opposing side walls;
a composite core extending axially, with respect to the centerline, through a respective portion of the dovetail portion and the airfoil portion;
a laminate skin extending axially, with respect to the centerline, from the radially inner surface and along a respective portion of the composite core and defining a respective portion of the side wall, the laminate skin defining a receptive portion of the radially inner surface; and
a roll snubber provided within the gap and on the radially inner surface, the roll snubber extending radially, with respect to the centerline, along the radially inner surface and at least radially to a transition between the composite core and the laminate skin, a contact between the roll snubber and the radially inner surface terminating radially along the laminate skin, with respect to the centerline, the roll snubber preventing the dovetail corner from contacting the slot during rotation of the composite airfoil assembly.