Continuous wedge vane arm with failsafe retention clip
A vane arm assembly for a gas turbine engine is provided including: a vane arm having a first end, a second end opposite the first end, and an aperture proximate the second end, the aperture being defined by 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 clip partially enclosing a portion of the second end of the vane arm 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 having a first end, a second end opposite the first end, and an aperture proximate the second end, the aperture being defined by an aperture wall;
a vane stem having a neck portion, the 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 clip partially enclosing a portion of the second end of the vane arm to provide redundant position retention of the vane arm in the longitudinal direction of the vane stem, wherein the impedance clip comprises:
a first side wall;
a second side wall opposite the first side wall;
a third side wall connecting the first side wall and the second side wall;
a first top wall attached to the first side wall, the first top wall being oriented about perpendicular to the first side wall;
a second top wall is attached to the second side wall, the second top wall being oriented about perpendicular to the second side wall,
wherein the first top wall and the second top wall includes a cut to wrap around the neck portion of the vane stem, and
wherein the first top wall and the second top wall include a tab that bends into the aperture of the vane arm proximate the neck portion of the vane stem.
2. The vane arm assembly of claim 1 , wherein the impedance clip is interposed between the mechanical fastener and the vane arm.
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.
6. The vane arm assembly of claim 4 , wherein the anti-rotation surface is disposed radially outwardly of the wedge face.
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 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 having a first end, a second end opposite the first end, and an aperture proximate the second end, the aperture being defined by an aperture wall;
a vane stem having a neck portion, the 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 clip partially enclosing a portion of the second end of the vane arm to provide redundant position retention of the vane arm in the longitudinal direction of the vane stem, wherein the impedance clip comprises:
a first side wall;
a second side wall opposite the first side wall;
a third side wall connecting the first side wall and the second side wall;
a first top wall attached to the first side wall, the first top wall being oriented about perpendicular to the first side wall;
a second top wall is attached to the second side wall, the second top wall being oriented about perpendicular to the second side wall,
wherein the first top wall and the second top wall include a cut out to wrap around the neck portion of the vane stem, and
wherein the first top wall and the second top wall include a tab that bends into the aperture of the vane arm proximate the neck portion of the vane stem.
9. The gas turbine engine of claim 8 , wherein the impedance clip is interposed between the mechanical fastener and the vane arm.
10. The gas turbine engine of claim 8 , wherein the vane arm assembly further comprises:
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.
11. The gas turbine engine of claim 10 , 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.
12. The gas turbine engine of claim 11 , wherein the anti-rotation wall is disposed radially outwardly of the angled face.
13. The gas turbine engine of claim 11 , wherein the anti-rotation surface is disposed radially outwardly of the wedge face.
14. The gas turbine engine 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.