US 12,146,422 B2
Gas turbine engine including a rotating blade assembly
Roberto Maddaleno, Lanzo Torinese (IT); and Matteo Renato Usseglio, Turin (IT)
Assigned to GE Avio S.r.l., Rivalta di Torino (IT)
Filed by GE Avio S.r.l, Rivalta di Torino (IT)
Filed on Aug. 16, 2022, as Appl. No. 17/888,539.
Claims priority of application No. 102021000029963 (IT), filed on Nov. 26, 2021.
Prior Publication US 2023/0167745 A1, Jun. 1, 2023
Int. Cl. F01D 5/30 (2006.01); F01D 5/22 (2006.01)
CPC F01D 5/3053 (2013.01) [F01D 5/225 (2013.01); F01D 5/3015 (2013.01); F01D 5/3069 (2013.01); F05D 2220/32 (2013.01); F05D 2230/60 (2013.01); F05D 2240/30 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A rotating blade assembly rotatable about a rotational axis, the rotating blade assembly comprising:
a disc including a seat having at least a portion of a first through hole;
a blade assembly having an upper platform, a lower platform, a dovetail extending from the lower platform, and a blade extending between the upper platform and the lower platform; and
a retainer assembly securing the disc to the blade assembly, the retainer assembly comprising:
an expandable hollow tubular element defining a second through hole, which is aligned with the first through hole, the expandable hollow tubular element including a tubular wall and a plurality of fingers extending axially, with respect to the rotational axis; and
a pin extending through at least a portion of the second through hole and the first through hole, and confronting at least a portion of the expandable hollow tubular element.