US 12,264,593 B1
Damped bladed rotor for gas turbine engine
Philippe Boyer, Saint Isidore (CA); Prakul Mittal, Longueuil (CA); Yashiva Dorsamy, St Hubert (CA); Jasrobin Grewal, Pincourt (CA); and Domenico Di Florio, Saint Lazare (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on Nov. 9, 2023, as Appl. No. 18/388,305.
Int. Cl. F01D 25/06 (2006.01); F01D 5/30 (2006.01)
CPC F01D 25/06 (2013.01) [F01D 5/30 (2013.01); F05D 2220/323 (2013.01); F05D 2240/30 (2013.01); F05D 2260/96 (2013.01)] 17 Claims
OG exemplary drawing
 
1. An assembly for a gas turbine engine, comprising:
an integrally bladed rotor rotatable about an axis, the integrally bladed rotor including a plurality of rotor blades and a rotor disk;
the plurality of rotor blades arranged circumferentially around and projecting radially out from the rotor disk; and
the rotor disk including a flange, a groove and a plurality of slots, the groove extending circumferentially around the axis within the flange, the groove projecting radially into the flange from an inner side of the flange, the plurality of slots arranged circumferentially about the axis along the groove, and each of the plurality of slots projecting radially into the flange from the inner side of the flange, wherein the groove projects radially into the flange from the inner side of the flange to an outer end of the groove, and each of the plurality of slots projects further radially into the flange from the outer end of the groove; and
a damper mounted to the rotor disk and seated within the groove.