US 12,305,528 B2
Rotor assembly for gas turbine engines with replaceable balance weight bands
Ryan C. Humes, Indianapolis, IN (US)
Assigned to Rolls-Royce North American Technologies Inc., Indianapolis, IN (US)
Filed by Rolls-Royce North American Technologies Inc., Indianapolis, IN (US)
Filed on Aug. 8, 2023, as Appl. No. 18/231,561.
Prior Publication US 2025/0052158 A1, Feb. 13, 2025
Int. Cl. F01D 5/02 (2006.01)
CPC F01D 5/027 (2013.01) [F05D 2240/24 (2013.01); F05D 2260/15 (2013.01); F05D 2260/30 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A rotor assembly adapted for use in a gas turbine engine, the rotor assembly comprising:
a first rotor arranged circumferentially about a central axis, the first rotor having a first rotor body that extends circumferentially about the central axis, a first band that extends axially away from the first rotor body at least partway circumferentially about the central axis, a plurality of first splines that extend radially inward from the first band, and a discrete first tab that extends axially away from the first band,
a second rotor arranged circumferentially about the central axis and located radially inward of the first rotor, the second rotor having a second rotor body that extends circumferentially about the central axis, a second band that extends at least partway circumferentially about the central axis, and a plurality of second splines that extend radially away from the band and engage with the plurality of first splines to couple the second rotor with the first rotor for rotation therewith, and
a balance weight located radially between the first rotor and the second rotor and configured to balance a weight distribution of the rotor assembly, the balance weight extending circumferentially partway about the central axis and formed to define a groove that receives the first tab of the first rotor to block circumferential movement of the balance weight relative to the first rotor and the second rotor, wherein an outer radial surface of the balance weight is configured to be machined as a sacrificial layer to allow for balance correction of the rotor assembly without machining the first rotor and the second rotor.