Bumper for synchronizing ring of gas turbine engine

Patent metadata

Field	Value
Publication number	US-9617869-B2
Application number	US-201414178849-A
Country	US
Kind code	B2
Filing date	Feb 12, 2014
Priority date	Feb 17, 2013
Publication date	Apr 11, 2017
Grant date	Apr 11, 2017

Abstract

A synchronizing assembly for a gas turbine engine has a synchronizing ring. A bumper assembly has a cradle and a bumper held within the cradle. The cradle is secured to the synchronizing ring by at least one fastener without the fastener extending through the bumper. An engine is also disclosed.

First claim

What is claimed is:

1. A synchronizing assembly for a gas turbine engine comprising:
a synchronizing ring to be attached to a case structure surrounding an engine axis; and
a bumper assembly comprising a cradle and a bumper held within the cradle, wherein the cradle is secured to the synchronizing ring by at least one fastener without the fastener extending through the bumper, and wherein the bumper includes a first surface and a second surface radially inward of the first surface, the first surface abutting against the synchronizing ring and the second surface abutting against the case structure.

2. The synchronizing assembly according to claim 1 wherein the cradle comprises a sheet metal piece.

3. The synchronizing assembly according to claim 1 wherein the bumper comprises a solid structure.

4. The synchronizing assembly according to claim 3 wherein the bumper is comprised of a composite material.

5. The synchronizing assembly according to claim 1 wherein the bumper comprises a base portion and a projection portion that extends radially inward of the base portion toward the engine axis, and wherein the base portion extends circumferentially beyond the projection portion to define a lip portion.

6. The synchronizing assembly according to claim 5 wherein the cradle includes a base with an opening extending through the base and tabs extending circumferentially from opposing ends of the base, wherein the tabs are radially outward of the base, and wherein the opening is surrounded by side edges, and wherein the lip portion rests on the side edges.

7. The synchronizing assembly according to claim 6 wherein the side edges comprise first and second side edges that define a length of the base and first and second end edges that define a width of the base, and including side walls extending radially outwardly from the first and second side edges and end walls extending radially outwardly from the first and second end edges.

8. The synchronizing assembly according to claim 1 wherein the cradle includes a base with a center opening surrounded by generally flat side edges, and wherein the bumper includes a base portion and a projection portion that extends in a radially inward direction from the base portion to form a lip portion that surrounds the projection portion, and wherein the projection portion extends through the center opening such that the lip portion rests on the flat side edges of the cradle.

9. The synchronizing assembly according to claim 8 wherein the bumper projects outwardly beyond a radially outermost surface of the cradle to directly abut against the synchronizing ring and beyond a radially innermost surface of the cradle to directly abut against the case structure.

10. The synchronizing assembly according to claim 8 wherein the cradle includes a pair of side walls extending radially outwardly from the base connected by a pair of end walls extending radially outwardly from the base, the side walls defining a length that is greater than a width of the end walls.

11. The synchronizing assembly according to claim 10 including a clearance feature at each intersection between one side wall and one end wall.

12. The synchronizing assembly according to claim 11 wherein the clearance feature comprises a recess at each corner of the center opening.

13. The synchronizing assembly according to claim 10 including a tab extending from each of the end walls, the tabs comprising an attachment interface for the at least one fastener, and wherein the tabs are located radially outwardly of the base.

14. The synchronizing assembly according to claim 13 wherein the at least one fastener comprises two fasteners, and wherein each tab includes one opening configured to receive one fastener.

15. A gas turbine engine comprising:
a compressor section surrounding an engine center axis and including a compressor case with at least one pad;
at least one stage of variable stator vanes associated with the compressor section; and
a synchronizing assembly that actuates the variable stator vanes, the synchronizing assembly including a synchronizing ring and a bumper assembly, the bumper assembly comprising a cradle and a bumper held within the cradle between the at least one pad and the synchronizing ring, and wherein the cradle is secured to the synchronizing ring by at least one fastener without the fastener extending through the bumper, and wherein the bumper includes a first surface that abuts against the synchronizing ring and a second surface radially inward of the first surface, the second surface abutting against the pad.

16. The gas turbine engine according to claim 15 wherein the bumper comprises a solid structure.

17. The gas turbine engine according to claim 15 wherein the bumper comprises a base portion and a projection portion that extends radially inward of the base portion toward the engine center axis, and wherein the base portion extends circumferentially beyond the projection portion to define a lip portion.

18. The gas turbine engine according to claim 17 wherein the cradle includes a base with an opening extending through the base and tabs extending circumferentially from opposing ends of the base, and wherein the tabs are radially outward of the base, and wherein the opening is surrounded by side edges, and wherein the lip portion rests on the side edges.

19. The gas turbine engine according to claim 18 wherein the side edges comprise first and second side edges that define a length of the base and first and second end edges that define a width of the base, and including side walls extending radially outwardly from the first and second side edges and end walls extending radially outwardly from the first and second end edges.

20. The gas turbine engine according to claim 15 wherein the cradle includes a base with a center opening surrounded by generally flat side edges, and wherein the bumper includes a base portion and a projection portion that extends in a radially inward direction from the base portion to form a lip portion that surrounds the projection portion, and wherein the projection portion extends through the center opening such that the lip portion rests on the flat side edges of the cradle.

21. The gas turbine engine according to claim 20 wherein the bumper projects outwardly beyond a radially outermost surface of the cradle to directly abut against the synchronizing ring and beyond a radially innermost surface of the cradle to directly abut against the compressor case.

22. The gas turbine engine according to claim 21 wherein the cradle includes a pair of side walls extending radially outwardly from the base connected by a pair of end walls extending radially outwardly from the base, the side walls defining a length that is greater than a width of the end walls.

23. The gas turbine engine according to claim 22 including a clearance feature at each intersection between one side wall and one end wall.

24. The gas turbine engine according to claim 22 including a tab extending from each of the end walls, the tabs comprising a fastener attachment interface, and wherein the tabs are located radially outwardly of the base, and wherein the at least one fastener comprises two fasteners, and wherein each tab includes one opening configured to receive one fastener.

Assignees

• United Technologies Corp

Inventors

• Leblanc Ryan Edward
• Gasmen Eugene C

Classifications

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F04D29/563

  specially adapted for elastic fluid pumps · 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

• Y10T29/49245

  Vane type or other rotary, e.g., fan · CPC title