Variable-pitch vane assembly

Patent metadata

Field	Value
Publication number	US-10815818-B2
Application number	US-201715653064-A
Country	US
Kind code	B2
Filing date	Jul 18, 2017
Priority date	Jul 18, 2017
Publication date	Oct 27, 2020
Grant date	Oct 27, 2020

Abstract

A variable-pitch vane assembly for a gas turbine engine includes a sync ring, a vane having a vane arm, and a pin installed through the sync ring and through the vane arm. The pin includes an anti-rotation notch located along a pin shaft. An anti-rotation spacer is engaged with the pin at the anti-rotation notch to prevent rotation of the pin. A turbine section of a gas turbine engine includes a turbine rotor and a turbine stator. The turbine stator includes one or more variable-pitch vane assemblies including a sync ring, a vane having a vane arm, and a pin installed through the sync ring and through the vane arm. The pin includes an anti-rotation notch located along a pin shaft. An anti-rotation spacer is engaged with the pin at the anti-rotation notch to prevent rotation of the pin.

First claim

What is claimed is:

1. A variable-pitch vane assembly for a gas turbine engine, comprising:
a sync ring;
a vane having a vane arm;
a pin installed through the sync ring and through the vane arm, the pin including an anti-rotation notch disposed along a pin shaft; and
an anti-rotation spacer engaged with the pin at the anti-rotation notch to prevent rotation of the pin;
wherein the pin has a threaded connection with one of the sync ring or a bushing disposed between the vane arm and the pin.

2. The variable-pitch vane assembly of claim 1 , wherein the pin has a recessed hexagonal head.

3. The variable-pitch vane assembly of claim 1 , wherein the anti-rotation spacer is disposed between a pin head and the vane arm.

4. The variable-pitch vane assembly of claim 1 , further comprising a locking tab washer to retain the anti-rotation spacer at the anti-rotation notch and/or engage with the anti-rotation notch.

5. The variable-pitch vane assembly of claim 1 , wherein the anti-rotation spacer has an L-shaped cross-section.

6. The variable-pitch vane assembly of claim 5 , wherein a first leg of the anti-rotation spacer engages the anti-rotation notch, and a second leg of the anti-rotation spacer abuts an outer ring surface of the sync ring.

7. A turbine section of a gas turbine engine, comprising:
a turbine rotor; and
a turbine stator, the turbine stator including one or more variable-pitch vane assemblies including:
a sync ring;
a vane having a vane arm;
a pin installed through the sync ring and through the vane arm, the pin including an anti-rotation notch disposed along a pin shaft; and
an anti-rotation spacer engaged with the pin at the anti-rotation notch to prevent rotation of the pin;
wherein the pin has a threaded connection with one of the sync ring or a bushing disposed between the vane arm and the pin.

8. The turbine section of claim 7 , wherein the pin has a recessed hexagonal head.

9. The turbine section of claim 7 , wherein the anti-rotation spacer is disposed between a pin head and the vane arm.

10. The turbine section of claim 7 , further comprising a locking tab washer to retain the anti-rotation spacer at the anti-rotation notch.

11. The turbine section of claim 7 , wherein the anti-rotation spacer has an L-shaped cross-section.

12. The turbine section of claim 11 , wherein a first leg of the anti-rotation spacer engages the anti-rotation notch, and a second leg of the anti-rotation spacer abuts an outer ring surface of the sync ring.

13. A method of assembling a variable-pitch vane assembly, comprising:
installing a pin through a sync ring and through a vane arm of a vane; and
installing an anti-rotation spacer such that the anti-rotation spacer engages an anti-rotation notch at the pin to retain the pin at the sync ring and the vane arm;
wherein the pin has a threaded connection with one of the sync ring or a bushing disposed between the vane arm and the pin.

14. The method of claim 13 , wherein installing the pin through the vane arm includes:
installing a bushing in a vane arm opening of the vane arm; and
installing the pin into the bushing.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Propheter-Hinckley Tracy A
• Surace Raymond
• Hazzard Robert L
• Borja Mark

Classifications

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• F05D2240/128

  Nozzles · CPC title

• F05D2260/50

  Kinematic linkage, i.e. transmission of position · 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

• F05D2230/60

  Assembly methods · CPC title