Cover for airfoil assembly for a gas turbine engine
A vane assembly includes a fixed airfoil portion that extends between a radially inner platform and radially outer platform and has a pressure side and a suction side. A rotatable airfoil portion is located aft of the fixed airfoil portion and has a pressure side and a suction side. A cover extends from the pressure side of the fixed airfoil portion to the pressure side of the rotatable airfoil portion.
1. A vane assembly comprising:
a fixed airfoil portion extending between a radially inner platform and a radially outer platform, the fixed airfoil portion having a pressure side, a suction side, a slot extending in a radical direction, and recess;
a rotatable airfoil portion aft of the fixed airfoil portion having a pressure side and a suction side and is rotatable about an axis that extends through the rotatable airfoil portion; and
a cover extending from the pressure side of the fixed airfoil portion to the pressure side of the rotatable airfoil portion, wherein a tab on the cover is at least partially located within the slot and the cover is accepted in the recess.
2. The vane assembly of claim 1 , wherein the cover is made of a flexible silicon material.
3. The vane assembly claim 1 , wherein the cover includes a first side facing in the same direction as the pressure side on the fixed airfoil portion and a second side opposite the first side in abutting contact with the recess.
4. The vane assembly of claim 1 , wherein a trailing edge of the fixed airfoil portion includes a concave surface and a leading edge of the rotatable airfoil portion is convex and follows a profile of the trailing edge of the fixed airfoil portion.
5. A gas turbine engine comprising:
a compressor section driven by a turbine section, wherein the compressor section includes a vane assembly having:
a fixed airfoil portion extending between a radially inner platform and a radially outer platform, the fixed airfoil portion having a pressure side, a suction side, a slot extending in a radical direction, and a recess;
a rotatable airfoil portion aft of the fixed airfoil portion having a pressure side and a suction side and is rotatable about an axis that extends through the rotatable airfoil portion; and
a cover extending from the pressure side of the fixed airfoil portion to the pressure side of the rotatable airfoil portion, wherein a tab on the cover is at least partially located within the slot and the cover is accepted in the recess.
6. The gas turbine engine claim 5 , wherein the cover is made of a flexible silicon material.
7. The gas turbine engine of claim 5 , wherein the cover includes a first side facing in the same direction as the pressure side on the fixed airfoil portion and a second side opposite the first side in abutting contact with the recess.
8. The gas turbine engine of claim 5 , wherein a trailing edge of the fixed airfoil portion includes a concave surface and a leading edge of the rotatable airfoil portion is convex and follows a profile of the trailing edge of the fixed airfoil portion.
9. A method of operating a variable vane assembly comprising the steps of:
rotating a rotatable airfoil portion relative to a fixed airfoil portion, wherein the rotatable airfoil portion is rotatable about an axis that extends through the rotatable airfoil portion and the fixed airfoil includes a slot extending in a radial direction;
flexing a cover in response to the relative movement of the rotatable airfoil portion relative to the fixed airfoil portion, wherein the cover extends axially from a pressure side of the fixed airfoil portion to a pressure side of the rotatable airfoil portion, wherein the cover includes a first side facing in the same direction as the pressure side on the fixed airfoil portion, a second side opposite the first side in abutting contact with the fixed airfoil portion, and a tab that extends into the slot.