US 12,467,365 B1
In situ balancing mass(es) for aircraft powerplant
Nathan Tomes, Hamilton (CA); Tyler Richardson, Toronto (CA); and Dave Menheere, Norval (CA)
Assigned to Pratt & Whitney Canada Corp., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Quebec (CA)
Filed on Jan. 27, 2025, as Appl. No. 19/038,559.
Int. Cl. F01D 5/02 (2006.01); F04D 29/66 (2006.01); F16F 15/32 (2006.01)
CPC F01D 5/027 (2013.01) [F04D 29/662 (2013.01); F05D 2220/323 (2013.01); F05D 2260/15 (2013.01); F05D 2260/31 (2013.01); F05D 2260/38 (2013.01); F16F 15/32 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An apparatus for an aircraft powerplant, comprising:
a rotating structure configured to rotate about an axis, the rotating structure including a bladed rotor, a first component, a second component, a first balancing mass, a second balancing mass and a spring element, wherein the first balancing mass and the second balancing mass are configured to rotationally balance the rotating structure about the axis;
the first component comprising a plurality of first component teeth;
the second component comprising a plurality of second component teeth;
the first balancing mass including a first mass ring and a plurality of first mass teeth, the first mass ring extending circumferentially about the axis, the plurality of first mass teeth arranged circumferentially about the axis and projecting axially out from the first mass ring, and the plurality of first mass teeth meshed with the plurality of first component teeth;
the second balancing mass including a second mass ring and a plurality of second mass teeth, the second mass ring extending circumferentially about the axis, the plurality of second mass teeth arranged circumferentially about the axis and projecting axially out from the second mass ring, and the plurality of second mass teeth meshed with the plurality of second component teeth; and
the spring element located axially between and engaged with the first balancing mass and the second balancing mass.