US 12,146,421 B2
Deformable root spacer for a gas turbine engine rotor blade
Colin J. Kling, Souderton, PA (US); and Nicholas J. Lawliss, West Hartford, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Oct. 28, 2022, as Appl. No. 17/976,345.
Prior Publication US 2024/0141794 A1, May 2, 2024
Int. Cl. F01D 11/00 (2006.01); F01D 5/30 (2006.01)
CPC F01D 5/30 (2013.01) [F01D 11/008 (2013.01); F05D 2220/32 (2013.01); F05D 2240/80 (2013.01); F05D 2250/70 (2013.01); F05D 2300/514 (2013.01)] 13 Claims
OG exemplary drawing
 
1. A rotor assembly, comprising:
a rotor disk including a slot;
a rotor blade including a blade root arranged within the slot; and
a root spacer arranged within the slot radially between the rotor disk and the blade root, the root spacer comprising a cellular structure with a plurality of internal cells;
the cellular structure including a first sidewall, a second sidewall and cellular core radially between and connected to the first sidewall and the second sidewall, the first sidewall engaging the blade root and overlapping the plurality of internal cells, and the second sidewall engaging the rotor disk and overlapping the plurality of internal cells; and
the cellular core including a plurality of core elements extending radially between the first sidewall and the second sidewall, each of the plurality of internal cells formed by and between a respective neighboring pair of the plurality of core elements, and an entirety of each of the plurality of core elements spaced from a respective neighboring one or more of the plurality of core elements.