US 12,467,383 B2
Joint for connection to variable guide vane of gas turbine engine
Richard Ivakitch, Scarborough (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Québec (CA)
Filed by Pratt & Whitney Canada Corp., Québec (CA)
Filed on Mar. 7, 2024, as Appl. No. 18/598,088.
Prior Publication US 2025/0283420 A1, Sep. 11, 2025
Int. Cl. F01D 17/16 (2006.01)
CPC F01D 17/162 (2013.01) [F05D 2240/50 (2013.01); F05D 2260/31 (2013.01); F05D 2260/50 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A variable pitch stator vane stage of a gas turbine engine, comprising:
a plurality of stator vanes extending across a flowpath of the gas turbine engine; and
an actuation assembly operably connected to the plurality of stator vanes, including:
an actuation ring extending circumferentially around an engine central longitudinal axis of the gas turbine engine; and
a plurality of vane links, each vane link operably connecting a corresponding stator vane of the plurality of stator vanes to the actuation ring, a vane link of the plurality of vane links including:
a link body; and
a first link end connected the link body, the first link end including a first spherical connection to the actuation ring;
wherein circumferential movement of the actuation ring about the engine central longitudinal axis urges rotation of the plurality of vanes about their respective vane axes; and
a vane arm operably connected to a vane stem of a vane of the plurality of vanes via a vane bolt and extending from the vane stem, the vane arm secured to a second link end of the vane link, the second link end including a spherical connection to the vane arm.