Airfoil assembly for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10808568-B2
Application number	US-201816128911-A
Country	US
Kind code	B2
Filing date	Sep 12, 2018
Priority date	Sep 12, 2018
Publication date	Oct 20, 2020
Grant date	Oct 20, 2020

Abstract

A vane assembly includes a rotatable airfoil that extends between a radially inner platform and a radially outer platform and has a leading edge and a trailing edge. A thrust projection is fixed relative to the rotatable airfoil. The thrust projection includes a first thrust surface for supporting radial loads in a first radial direction and a second thrust surface for supporting radial loads in a second direction.

First claim

What is claimed is:

1. A vane assembly comprising:
a rotatable airfoil extending between a radially inner platform and a radially outer platform having a leading edge and a trailing edge;
a radially inward directed protrusion extending radially inward from the rotatable airfoil;
a thrust projection fixed relative to the rotatable airfoil and located radially inward from the radially inward directed protrusion, wherein the thrust projection includes a first thrust surface for supporting radial loads in a first radial direction and a second thrust surface for supporting radial loads in a second radial direction and the first or second thrust surface encircles a perimeter of the radially inward directed protrusion and the thrust projection includes a relatively constant outer diameter; and
a pivoting projection located on an opposite side of the thrust projection from the radially inward directed protrusion.

2. The vane assembly of claim 1 , wherein the rotatable airfoil is rotatable about an axis that extends through the rotatable airfoil and a center of the thrust projection.

3. The vane assembly of claim 2 , wherein the first thrust surface is a radially outer surface and the second thrust surface is a radially inner surface and the first thrust surface is connected to the second thrust surface by a cylindrical portion and the first and second thrust surfaces each form a ring between cylindrical portion and the radially inward directed protrusion.

4. The vane assembly of claim 2 , further comprising a radially outer projection on the rotatable airfoil having a cylindrical cross-section.

5. The vane assembly of claim 4 , wherein the radially outer projection extends through an opening in at least one of the radially outer platform or an engine case, the rotatable airfoil is rotatable relative to the radially outer platform and the radially inner platform, and the radially outer projection and the thrust projection are integral and single piece with the rotatable airfoil.

6. The vane assembly of claim 5 , further comprising a pivoting projection located radially inward from the thrust projection forming an integral single piece component with the thrust projection.

7. The vane assembly of claim 1 , further comprising a fixed airfoil portion extending between the radially inner platform and the radially outer platform having a leading edge and a trailing edge, wherein the rotatable airfoil is located aft of the fixed airfoil portion and the trailing edge of the fixed airfoil portion includes a concave surface.

8. The vane assembly of claim 7 , wherein the trailing edge of the fixed airfoil portion includes a first edge adjacent a pressure side of the fixed airfoil portion and a second edge adjacent a suction side of the fixed airfoil portion and the first edge and the second edge define boundaries of the concave surface.

9. The vane assembly of claim 8 , wherein the leading edge of the rotatable airfoil is convex and follows a profile of the concave surface on the fixed airfoil portion.

10. A gas turbine engine comprising:
a compressor section driven by a turbine section, wherein the compressor section includes a vane assembly having:
a rotatable airfoil extending between a radially inner platform and a radially outer platform having a leading edge and a trailing edge;
a thrust projection fixed relative to the rotatable airfoil, wherein the thrust projection includes a first thrust surface for supporting radial loads in a first radial direction and a second thrust surface for supporting radial loads in a second radial direction, wherein the first thrust surface is connected to the second thrust surface by a cylindrical portion and the first and second surfaces each form a ring and the thrust projection includes a relative constant outer diameter; and
a pivoting projection located on an opposite side of the thrust projection from the rotatable airfoil.

11. The gas turbine engine of claim 10 , wherein the rotatable airfoil is rotatable about an axis that extends through the rotatable airfoil and a center of the thrust projection.

12. The gas turbine engine of claim 11 , wherein the first thrust surface is a radially outer surface and the second thrust surface is a radially inner surface.

13. The gas turbine engine of claim 12 , further comprising a radially outer projection on the rotatable airfoil having a cylindrical cross-section.

14. The gas turbine engine of claim 13 , wherein the radially outer projection extends through an opening in at least one of the radially outer platform or an engine case, the rotatable airfoil is rotatable relative to the radially outer platform and the radially inner platform, and the radially outer projection and the thrust projection are integral with the rotatable airfoil.

15. The gas turbine engine of claim 10 , further comprising a fixed airfoil portion extending between the radially inner platform and the radially outer platform having a leading edge and a trailing edge, wherein the rotatable airfoil is located aft of the fixed airfoil portion, the trailing edge of the fixed airfoil portion includes a concave surface, the trailing edge of the fixed airfoil portion includes a first edge adjacent a pressure side of the fixed airfoil portion and a second edge adjacent a suction side of the fixed airfoil portion, and the first edge and the second edge define boundaries of the concave surface.

16. The gas turbine engine of claim 15 , wherein the leading edge of the rotatable airfoil is convex and follows a profile of the concave surface on the fixed airfoil portion.

17. The gas turbine engine of claim 10 , further comprising a radially inward directed protrusion extending radially inward from the rotatable airfoil with the thrust projection located radially inward from the radially inward directed protrusion with one of the first or second thrust surfaces encircles a perimeter of the radially inward directed protrusion and the radially outer projection and the thrust projection are integral with the rotatable airfoil.

18. A method of controlling radial loads in a vane assembly comprising the steps of:
resisting a first radial load on the vane assembly in a first radial direction with a first thrust surface forming a ring on a thrust projection on a rotatable airfoil; and
resisting a second radial load in a second radial direction with a second thrust surface forming a ring on the thrust projection on the rotatable airfoil, wherein the first thrust surface and the second thrust surface are located on a thrust projection having a relatively constant outer diameter and spaced from an airfoil, and a pivoting projection is located on an opposite side of the thrust projection from the airfoil.

19. The method of claim 18 , wherein the first thrust surface and the second thrust surface are each in contact with a radially inner platform and a retention clam shell.

20. The method of claim 19 , wherein the vane assembly includes a fixed airfoil portion having a leading edge and a trailing edge, the rotatable airfoil includes a leading edge and a trailing edge, and the rotatable airfoil and the fixed airfoil portion form a single vane.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Dyer David M
• Ronan Michael
• Knechtel Kevin

Classifications

• F04D29/323

  adjustable · CPC title

• F01D5/146

  of blades with tandem configuration, split blades or slotted blades · CPC title

• F04D29/544

  Blade shapes · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F05B2240/31

  of changeable form or shape · CPC title