SELF-RETAINING VANE ARM ASSEMBLY FOR GAS TURBINE ENGINE
A vane arm assembly for a gas turbine engine. The vane arm assembly includes a vane arm defining an aperture at an end thereof with an aperture wall. The vane arm assembly also includes a vane stem extending through the aperture of the vane arm. The vane arm assembly further includes a mechanical fastener retaining a position of the vane arm in the longitudinal direction of the vane stem. The vane arm assembly yet further includes an impedance ring disposed within the aperture of the vane arm and within an impedance ring groove defined by the vane stem to provide redundant position retention of the vane arm in the longitudinal direction of the vane stem.
1 . A vane arm assembly for a gas turbine engine comprising:
a vane arm defining an aperture at an end thereof with an aperture wall;
a vane stem extending through the aperture of the vane arm;
a mechanical fastener retaining a position of the vane arm in the longitudinal direction of the vane stem; and
an impedance ring disposed within the aperture of the vane arm and within an impedance ring groove defined by the vane stem to provide redundant position retention of the vane arm in the longitudinal direction of the vane stem.
2 . The vane arm assembly of claim 1 , wherein the aperture wall of the vane arm includes an impedance ring surface extending at least partially around the aperture wall, the impedance ring disposed on the impedance ring surface.
3 . The vane arm assembly of claim 1 , further comprising:
an angled face disposed on an exterior of the vane stem; and
a wedge face disposed on the aperture wall, the wedge face and the angled face having a corresponding geometry, the wedge face and the angled face in contact with each other in a preloaded condition to transmit torque from the vane arm to the vane stem.
4 . The vane arm assembly of claim 3 , further comprising:
an anti-rotation wall disposed on the exterior of the vane stem, the anti-rotation wall angularly offset from the angled face of the vane stem; and
an anti-rotation surface disposed on the aperture wall and angularly offset from the wedge face of the vane arm, the anti-rotation wall and the anti-rotation surface having a corresponding geometry, the anti-rotation wall and the anti-rotation surface in contact with each other to maintain torque transmission from the vane arm to the vane stem during a surge condition.
5 . The vane arm assembly of claim 4 , wherein the anti-rotation wall is disposed radially outwardly of the angled face, and the impedance ring groove is disposed radially outwardly of the anti-rotation wall.
6 . The vane arm assembly of claim 4 , wherein the anti-rotation surface is disposed radially outwardly of the wedge face, and the impedance ring is positioned radially outwardly of the anti-rotation surface.
7 . The vane arm assembly of claim 1 , wherein the vane arm is operatively coupled to an actuator ring with a pin proximate to a first end of the vane arm, the vane arm operatively coupled to the vane stem proximate a second end of the vane arm to actuate movement of at least one adjustable guide vane in the gas turbine engine.
8 . A vane arm assembly for a gas turbine engine comprising:
a vane arm defining an aperture at an end thereof with an aperture wall;
a vane stem extending through the aperture of the vane arm;
an angled face disposed on an exterior of the vane stem;
a wedge face disposed on the aperture wall, the wedge face and the angled face having a corresponding geometry, the wedge face and the angled face in contact with each other in a preloaded condition to transmit torque from the vane arm to the vane stem;
an anti-rotation wall disposed on the exterior of the vane stem, the anti-rotation wall angularly offset from the angled face of the vane stem; and
an anti-rotation surface disposed on the aperture wall and angularly offset from the wedge face of the vane arm, the anti-rotation wall and the anti-rotation surface having a corresponding geometry, the anti-rotation wall and the anti-rotation surface in contact with each other to maintain torque transmission from the vane arm to the vane stem during a surge condition.
9 . The vane arm assembly of claim 8 , further comprising:
a mechanical fastener retaining a position of the vane arm in the longitudinal direction of the vane stem; and
an impedance ring disposed within the aperture of the vane arm and within an impedance ring groove defined by the vane stem to provide redundant position retention of the vane arm in the longitudinal direction of the vane stem.
10 . The vane arm assembly of claim 9 , wherein the aperture wall of the vane arm includes an impedance ring surface extending at least partially around the aperture wall, the impedance ring disposed on the impedance ring surface.
11 . The vane arm assembly of claim 9 , wherein the anti-rotation wall is disposed radially outwardly of the angled face, and the impedance ring groove is disposed radially outwardly of the anti-rotation wall.
12 . The vane arm assembly of claim 9 , wherein the anti-rotation surface is disposed radially outwardly of the wedge face, and the impedance ring is positioned radially outwardly of the anti-rotation surface.
13 . The vane arm assembly of claim 8 , wherein the vane arm is operatively coupled to an actuator ring with a pin proximate to a first end of the vane arm, the vane arm operatively coupled to the vane stem proximate a second end of the vane arm to actuate movement of at least one adjustable guide vane in the gas turbine engine.
14 . A gas turbine engine comprising:
a compressor section;
a combustor section;
a turbine section; and
a vane arm assembly operatively coupled to an actuator ring and to at least one adjustable guide vane in the compressor section, the vane arm assembly comprising:
a vane arm defining an aperture at an end thereof with an aperture wall;
a vane stem extending through the aperture of the vane arm;
an angled face disposed on an exterior of the vane stem; and
a wedge face disposed on the aperture wall, the wedge face and the angled face having a corresponding geometry, the wedge face and the angled face in contact with each other in a preloaded condition to transmit torque from the vane arm to the vane stem;
an anti-rotation wall disposed on the exterior of the vane stem, the anti-rotation wall angularly offset from the angled face of the vane stem;
an anti-rotation surface disposed on the aperture wall and angularly offset from the wedge face of the vane arm, the anti-rotation wall and the anti-rotation surface having a corresponding geometry, the anti-rotation wall and the anti-rotation surface in contact with each other to maintain torque transmission from the vane arm to the vane stem during a surge condition;
a mechanical fastener retaining a position of the vane arm in the longitudinal direction of the vane stem; and
an impedance ring disposed within the aperture of the vane arm and within an impedance ring groove defined by the vane stem to provide redundant position retention of the vane arm in the longitudinal direction of the vane stem.
15 . The gas turbine engine of claim 14 , wherein the aperture wall of the vane arm includes an impedance ring surface extending at least partially around the aperture wall, the impedance ring disposed on the impedance ring surface.
16 . The gas turbine engine of claim 14 , wherein the anti-rotation wall is disposed radially outwardly of the angled face, and the impedance ring groove is disposed radially outwardly of the anti-rotation wall.
17 . The gas turbine engine of claim 14 , wherein the anti-rotation surface is disposed radially outwardly of the wedge face, and the impedance ring is positioned radially outwardly of the anti-rotation surface.