Joint for connection to variable guide vane of gas turbine engine
A variable pitch stator vane stage of a gas turbine engine includes a plurality of stator vanes extending across a flowpath of the gas turbine engine, and an actuation assembly operably connected to the plurality of start vanes. The actuation assembly includes 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 connects a corresponding stator vane of the plurality of stator vanes to the actuation ring. A vane link of the plurality of vane links includes a link body, and a first link end connected the link body. The first link end includes a first spherical connection to the actuation ring. Circumferential movement of the actuation ring about the engine central longitudinal axis urges rotation of the plurality of vanes about their respective vane axes.
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.
2 . The variable pitch stator vane stage of claim 1 , wherein the first link end includes:
a first eye; and
a first spherical bearing element disposed in the first eye;
wherein the vane link is connected to the actuation ring through the first spherical bearing member.
3 . The variable pitch stator vane stage of claim 2 , further comprising a first link fastener extending through the actuation ring and the first spherical bearing member thereby connecting the vane link to the actuation ring.
4 . The variable pitch stator vane stage of claim 1 , wherein a length of the vane link is adjustable.
5 . The variable pitch stator vane stage of claim 4 , wherein the length of the vane link is adjustable via a threaded connection of the link body to the first link end.
6 . The variable pitch stator vane stage of claim 1 , wherein the second link end includes:
a second eye; and
a second spherical bearing member disposed in the second eye;
wherein the vane link is connected to the vane arm through the second spherical bearing member.
7 . The variable pitch stator vane stage of claim 6 , further comprising a second link fastener extending through the vane arm and the second spherical bearing member thereby connecting the vane link to the vane arm.
8 . A compressor section of a gas turbine engine, comprising:
one or more rotor stages configured to rotate about an engine central longitudinal axis;
one or more stator stages, the one or more stator stages including a variable pitch stator vane stage including:
a plurality of stator vanes extending across a flowpath of the gas turbine engine; and
an actuation assembly operably connected to the plurality of start stator vanes, including:
an actuation ring extending circumferentially around the 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.
9 . The compressor section of claim 8 , wherein the first link end includes:
a first eye; and
a first spherical bearing member disposed in the first eye;
wherein the vane link is connected to the actuation ring through the first spherical bearing member.
10 . The compressor section of claim 9 , further comprising a first link fastener extending through the actuation ring and the first spherical bearing member thereby connecting the vane link to the actuation ring.
11 . The compressor section of claim 8 , wherein a length of the vane link is adjustable.
12 . The compressor section of claim 11 , wherein the length of the vane link is adjustable via a threaded connection of the link body to the first link end.
13 . The compressor section of claim 8 , wherein the second link end includes:
a second eye; and
a second spherical bearing member disposed in the second eye;
wherein the vane link is connected to the vane arm through the second spherical bearing member.
14 . The compressor section of claim 13 , further comprising a second link fastener extending through the vane arm and the second spherical bearing member thereby connecting the vane link to the vane arm.
15 . A gas turbine engine, comprising:
a combustor section;
a turbine section driven by products of the combustion section;
a compressor section driven by rotation of the turbine section; and
a variable pitch stator vane stage disposed at at least one of the turbine section and the compressor section, the variable pitch stator vane stage, including:
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.
16 . The gas turbine engine of claim 15 , wherein the first link end includes:
a first eye; and
a first spherical bearing member disposed in the first eye;
wherein the vane link is connected to the actuation ring through the first spherical bearing member.
17 . The gas turbine engine of claim 16 , further comprising a first link fastener extending through the actuation ring and the first spherical bearing member thereby connecting the vane link to the actuation ring.
18 . The gas turbine engine of claim 15 , wherein a length of the vane link is adjustable via a threaded connection of the link body to the first link end.