US 11,674,435 B2
Levered counterweight feathering system
Nicholas M. Daggett, Cincinnati, OH (US); Gert Johannes van der Merwe, Lebanon, OH (US); Daniel Alan Niergarth, Norwood, OH (US); and Brian Lewis Devendorf, Georgetown, MA (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Jun. 29, 2021, as Appl. No. 17/361,804.
Prior Publication US 2022/0412254 A1, Dec. 29, 2022
Int. Cl. F02C 3/06 (2006.01); F02C 9/58 (2006.01); F02K 3/06 (2006.01)
CPC F02C 3/06 (2013.01) [F02C 9/58 (2013.01); F02K 3/06 (2013.01); F05D 2220/32 (2013.01); F05D 2220/36 (2013.01)] 18 Claims
OG exemplary drawing
 
15. A counterweight assembly for use in a gas turbine engine, the counterweight assembly comprising:
a link arm configured to couple with a pitch change mechanism of the gas turbine engine, a trunnion of a fan assembly of the gas turbine engine, or both, wherein the link arm is configured to drive rotation of the trunnion when coupled to the pitch change mechanism, the trunnion, or both;
a lever arm connected to the link arm;
a hinge pivotably connected to the lever arm, wherein the lever arm is disposed to rotate about a connection point of the lever arm and the hinge; and
a counterweight mounted to the lever arm at a location spaced from the hinge, wherein the counterweight is configured to move in response to a change in centrifugal load applied to the counterweight during operation of the gas turbine engine, wherein the link arm is connected to the actuation device, and wherein the actuation device comprises:
a first piece disposed to remain still relative to the fan disk; and
a second piece configured to move relative to the first piece, wherein the link arm is configured to drive a linear translation of the second piece in response to a translation of the counterweight.