Cover for airfoil assembly for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10934883-B2
Application number	US-201816128948-A
Country	US
Kind code	B2
Filing date	Sep 12, 2018
Priority date	Sep 12, 2018
Publication date	Mar 2, 2021
Grant date	Mar 2, 2021

Abstract

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.

First claim

What is claimed is:

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.

Assignees

• United Technologies Corp
• Raytheon Tech

Inventors

• Dyer David M
• Gammons Scott

Classifications

• F04D29/023

  especially adapted for elastic fluid pumps · CPC title

• F05D2300/30

  Inorganic materials other than provided for in groups F05D2300/10 - F05D2300/2291 · CPC title

• F01D17/162 Primary

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F04D29/544

  Blade shapes · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title