US 12,241,383 B2
Turbine engine with a composite-airfoil assembly having a dovetail portion
Benjamin Thomas Van Oflen, Cincinnati, OH (US); Gary Willard Bryant, Jr., Loveland, OH (US); Nicholas Joseph Kray, Mason, OH (US); Arthur William Sibbach, Boxford, MA (US); Michael John Franks, Cincinnati, OH (US); and Elzbieta Kryj-Kos, Liberty Township, OH (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. 18/173,952.
Prior Publication US 2024/0287906 A1, Aug. 29, 2024
Int. Cl. F01D 11/00 (2006.01); F01D 5/14 (2006.01); F01D 5/26 (2006.01); F01D 5/28 (2006.01); F01D 5/32 (2006.01); F01D 9/04 (2006.01)
CPC F01D 5/147 (2013.01) [F01D 5/282 (2013.01); F01D 5/323 (2013.01); F01D 5/326 (2013.01); F01D 9/041 (2013.01); F01D 11/008 (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,
a composite airfoil assembly extending between a leading edge and a trailing edge, the composite airfoil assembly comprising:
an airfoil portion extending radially outward from the periphery; and
a dovetail portion extending from the airfoil portion and being slidably received within the slot and terminating in a radially inner surface, the radially inner surface being spaced from the inner slot face to define a gap and extending an axial distance to define a dovetail span; and
a pitch snubber extending radially outward from the inner slot face and terminating radially within the gap at a snubber face, the pitch snubber extending radially into the gap and having a total axial length that is greater than 0% and less than or equal to 50% of the dovetail span, with at least a portion of the snubber face being configured to contact one of a respective portion of the inner radially surface when a force is applied to the composite airfoil assembly causing the composite airfoil assembly to rotate about a pitch axis.
 
12. 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;
a composite airfoil assembly extending between a leading edge and a trailing edge, the composite airfoil assembly comprising:
an airfoil portion extending radially outward from the periphery; and
a dovetail portion extending from the airfoil portion and being slidably received within the slot and terminating in a radially inner surface, the radially inner surface being spaced from the inner slot face to define a gap and extending an axial distance to define a dovetail span; and
a pitch snubber extending radially outward from the inner slot face and terminating radially at a snubber face within the gap, the pitch snubber being integrally formed with the disk, with at least a portion of the snubber face being configured to contact one of a respective portion of the slot or the inner surface when a force is applied to the composite airfoil assembly causing the composite airfoil assembly to rotate about a pitch axis.
 
13. 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;
a composite airfoil assembly extending between a leading edge and a trailing edge, the composite airfoil assembly comprising:
an airfoil portion extending radially outward from the periphery; and
a dovetail portion extending from the airfoil portion and being slidably received within the slot and terminating in a radially inner surface, the radially inner surface being spaced from the inner slot face to define a gap and extending an axial distance to define a dovetail span; and
a pitch snubber extending radially outward from the inner slot face and terminating radially within the gap at a snubber face, the snubber face being spaced a non-zero radial distance from an opposing portion of one of the slot or the radially inner surface to define the gap therebetween, with at least a portion of the snubber face being configured to contact one of a respective portion of the slot or the radially inner surface when a force is applied to the composite airfoil assembly causing the composite airfoil assembly to rotate about a pitch axis.