US 11,655,719 B2
Airfoil assembly
Matthew Mark Weaver, Loveland, OH (US); Dennis Paul Dry, Cincinnati, OH (US); and Todd William Bachmann, Edgewood, KY (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Apr. 16, 2021, as Appl. No. 17/232,721.
Prior Publication US 2022/0333491 A1, Oct. 20, 2022
Int. Cl. F01D 5/26 (2006.01); F01D 5/30 (2006.01); F01D 5/10 (2006.01)
CPC F01D 5/26 (2013.01) [F01D 5/10 (2013.01); F01D 5/3046 (2013.01); F01D 5/3084 (2013.01); F05D 2240/11 (2013.01); F05D 2300/6033 (2013.01)] 18 Claims
OG exemplary drawing
 
1. An airfoil assembly for a turbine engine defining an axial direction, a radial direction, and a circumferential direction, the airfoil assembly comprising:
a first airfoil defining a first end along the radial direction;
a first hub disposed on the first end of the first airfoil and comprising a first extension member extending at least partially in the radial direction;
a second airfoil adjacent to the first airfoil, the second airfoil defining a first end along the radial direction;
a second hub disposed on the first end of the second airfoil and comprising a second extension member extending at least partially in the radial direction; and
a circumferential bias assembly operable with the first extension member and the second extension member for exerting a circumferential force on at least one of the first extension member or the second extension member,
wherein the circumferential bias assembly is a first shroud assembly,
wherein the first shroud assembly comprises a first spring member coupled to the first extension member, positioned adjacent to the first extension member, or both,
wherein the first extension member is part of a first pair of extension members spaced apart in the axial direction to define a first space therebetween, and
wherein the first shroud assembly is disposed in the first space between the first pair of extension members.