Vane arm for variable vanes

Patent metadata

Field	Value
Publication number	US-11255217-B2
Application number	US-201916573001-A
Country	US
Kind code	B2
Filing date	Sep 17, 2019
Priority date	Sep 17, 2019
Publication date	Feb 22, 2022
Grant date	Feb 22, 2022

Abstract

A variable vane actuation system for a gas turbine engine includes a stem section that forms a base and a contoured section that extends from the base along an axis. A vane arm comprising a claw section received onto the contoured section and a fastener fastened to the contoured section to load the claw section to the base.

First claim

What is claimed is:

1. A variable vane actuation system for a gas turbine engine, comprising:
a stem section of a vane that forms a base and a contoured section that extends from the base along an axis;
a vane arm comprising a claw section received onto the contoured section, the claw section comprises opposing fingers that are curved from an upper surface, the upper surface comprises a contoured aperture to receive the contoured section providing a rotational lock interface, wherein the opposing fingers each terminate at respective faces spaced from each other to define a claw opening that receives the contoured section, the faces configured to interface directly with opposing sides of the contoured section; and
a fastener that extends through the contoured aperture and into the contoured section which compresses the opposing fingers of the claw section along the axis, a distance between the upper surface and the opposing fingers subsequent to installing the fastener is less than a distance between the upper surface and the opposing fingers prior to installing the fastener.

2. The system as recited in claim 1 , wherein the contoured section and the contoured aperture are non-circular shaped.

3. The system as recited in claim 1 , wherein the vane is rotatable about the axis.

4. The system as recited in claim 1 , wherein the stem extends from an outer trunnion of the vane.

5. The system as recited in claim 4 , wherein the vane comprises an airfoil.

6. The system as recited in claim 1 , wherein the claw section is manufactured of sheet metal that is between 40-70 mils (1.0-1.8 mm) thick.

7. The system as recited in claim 6 , wherein a difference in profile defines the base atop the stem section.

8. The system as recited in claim 6 , wherein the stem section extends from the vane through an engine case.

9. The system as recited in claim 1 , wherein the outer diameter of the stem section is greater than an outer profile of the contoured section.

10. The system as recited in claim 1 , wherein the contoured section and the contoured aperture are race-track shaped.

11. A method of assembling a variable vane actuation system, comprising:
preloading a claw section of a vane arm onto a base of a stem section of a vane along an axis of rotation of the stem section such that a contoured aperture of the claw section receives a contoured section of the stem section providing a rotational lock interface, wherein the preloading is performed by threading a fastener into a threaded bore in the stem section along the axis such that a distance between an upper surface of the claw section and opposing fingers of the claw section subsequent to installing the fastener is less than a distance between the upper surface and the opposing fingers prior to installing the fastener, wherein the fastener compresses the opposing fingers of the claw section along the axis.

12. The method as recited in claim 11 , further comprising providing the rotational lock interface between the upper surface of the claw section and the contoured section that extends from the base.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Landry Daniel R

Classifications

• 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

• F04D29/563

  specially adapted for elastic fluid pumps · CPC title

• F05D2260/50

  Kinematic linkage, i.e. transmission of position · CPC title

• F05D2260/74

  by turning around an axis perpendicular the rotor centre line · CPC title

• F05D2220/32

  in gas turbines · CPC title