Bellcrank for a variable vane assembly

• US 9,151,178 B2
• Filed: 11/15/2012
• Issued: 10/06/2015
• Est. Priority Date: 11/15/2012
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Holchin, John, Boyer, Mark, Harding, Tim
• Primary Examiner(s): Kershteyn, Igor
• Application Number:
  US13/678,433
• Publication Number:
  US 20140133968A1
• Time in Patent Office: 1,055 Days
• US Class Current: 1/1
• CPC Class Codes: F01D 17/162 for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line F01D17/167 takes precedence
• CPC Class Codes: F05D 2260/50 Kinematic linkage, i.e. transmission of position
• CPC Class Codes: F16C 2360/23 Gas turbine engines in general F02C
• CPC Class Codes: F16C 3/12 releasably connected
• CPC Class Codes: F16C 3/22 Cranks; Eccentrics constructional features of crank-pins F16C11/02
• CPC Class Codes: Y10T 29/49323 Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles
• CPC Class Codes: Y10T 29/49948 Multipart cooperating fastener [e.g., bolt and nut]
• CPC Class Codes: Y10T 29/49959 Nonresilient fastener

Abstract

A variable vane assembly for use in a gas turbine engine includes a variable vane, an actuator, and a mechanical linkage. The mechanical linkage connects the variable vane to the actuator. The mechanical linkage includes a bellcrank rotatable about an axis, a first bellcrank arm having a first clevis at an inner end, and a first pin extending through the first clevis and a first flange of the bellcrank to fasten the first bellcrank arm to the bellcrank.

Claims

1. A gas turbine engine comprising:

a flow path; and

a variable vane assembly comprising;

a variable vane positioned in the flow path and rotatable about an axis of the variable vane;

an actuator; and

a mechanical linkage connecting the variable vane to the actuator, the mechanical linkage comprising;

a bellcrank rotatable about an axis;

a first bellcrank arm having a first clevis at an inner end; and

a first pin extending through the first clevis and a first flange of the bellcrank to fasten the bellcrank arm to the bellcrank.

2. The gas turbine engine of claim 1, wherein the gas turbine engine is an industrial gas turbine engine comprising:

a low pressure compressor section including the variable vane assembly; and

a power turbine section positioned downstream of the low compressor section.

3. The gas turbine engine of claim 1, wherein the first bellcrank arm includes a second clevis at an outer end, and wherein the second clevis is oriented 90 degrees from the first clevis, and wherein the actuator is connected to the second clevis.

4. The gas turbine engine of claim 3, wherein the mechanical linkage further comprises:

a second bellcrank arm having a third clevis and a fourth clevis; and

a second pin extending through the third clevis and through a second flange on the bellcrank to fasten the second bellcrank arm to the bellcrank.

5. The gas turbine engine of claim 4, wherein the mechanical linkage further comprises:

a variable vane arm connected to a spindle of the variable vane;

a synchronization ring connected to the variable vane arm; and

a link arm connecting the fourth clevis to the synchronization ring, wherein the variable vane rotates in response to the actuator rotating the bellcrank.

6. The gas turbine engine of claim 1, wherein the variable vane is one of a first stage of variable vanes, wherein the first bellcrank arm connects the bellcrank to the first stage of variable vanes, the mechanical linkage further comprising:

a second bellcrank arm having a second clevis connected to a second flange of the bellcrank, wherein the second bellcrank arm connects the bellcrank to a second stage of variable vanes; and

a third bellcrank arm having a third clevis connected to a third flange of the bellcrank, wherein the third bellcrank arm connects the bellcrank to the actuator.

7. A variable vane assembly for use in a gas turbine engine, the variable vane assembly comprising:

a variable vane;

an actuator; and

a mechanical linkage connecting the variable vane to the actuator, the mechanical linkage comprising;

a bellcrank rotatable about an axis;

a first bellcrank arm having a first clevis at an inner end; and

a first pin extending through the first clevis and a first flange of the bellcrank to fasten the first bellcrank arm to the bellcrank.

8. The variable vane assembly of claim 7, wherein the first pin is angled with respect to an axis of the first bellcrank arm.

9. The variable vane assembly of claim 7, wherein the first bellcrank arm connects the bellcrank to the variable vane, the mechanical linkage further comprising:

a second bellcrank arm having a second clevis connected to a second flange of the bellcrank, wherein the second bellcrank arm connects the bellcrank to the actuator.

10. The variable vane assembly of claim 7, wherein the first clevis includes first and second ears and wherein the first flange is positioned between the first and second ears.

11. The variable vane assembly of claim 7, wherein the first bellcrank arm comprises a first dowel hole, wherein the bellcrank comprises a second dowel hole, and further comprising:

a dowel pin positioned at least partially in each of the first and second dowel holes.

12. The variable vane assembly of claim 11, wherein the first pin is a bolt, and wherein the first and second dowel holes are substantially perpendicular to the bolt.

13. The variable vane assembly of claim 11, wherein the first and second dowel holes are substantially perpendicular to the axis of the bellcrank.

14. A method of assembling a variable vane assembly for use in a gas turbine engine, the method comprising:

positioning a flange of a bellcrank in a clevis of a bellcrank arm; and

inserting a pin through the flange and the clevis to connect the bellcrank arm to the bellcrank.

15. The method of claim 14, and further comprising:

aligning a first hole on the flange with second and third holes on first and second respective ears of the clevis prior to inserting the pin.

16. The method of claim 15, wherein the pin is a bolt, wherein the flange fits loosely between first and second ears of the clevis when first positioned in the clevis, and further comprising:

threading a nut on the bolt; and

tightening the nut such that the first and second ears of the clevis are in contact with sides of the flange.

17. The method of claim 14, wherein the pin is a bolt, and further comprising:

inserting a dowel pin through a first dowel hole in the bellcrank arm and through a second dowel hole in the bellcrank.

18. The method of claim 14, wherein the clevis is a first clevis at an inner end of the bellcrank arm, and further comprising:

connecting a second clevis at an outer end of the bellcrank arm to an actuator.

19. The method of claim 14, wherein the clevis is a first clevis at an inner end of the bellcrank arm, and further comprising:

connecting a second clevis at an outer end of the bellcrank arm to a link arm.

20. The method of claim 19, and further comprising:

connecting the link arm to a synchronization ring;

connecting the synchronization ring to a plurality of variable vane arms; and

connecting the plurality of variable vane arms to a plurality of variable vanes, wherein the plurality of variable vanes rotate in response to rotation of the bellcrank.