Gas turbine engine synchronization ring

Patent metadata

Field	Value
Publication number	US-9422825-B2
Application number	US-201213668683-A
Country	US
Kind code	B2
Filing date	Nov 5, 2012
Priority date	Nov 5, 2012
Publication date	Aug 23, 2016
Grant date	Aug 23, 2016

Abstract

A synchronization ring for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a synchronization ring for a variable vane assembly. A plurality of rollers are attached to the synchronization ring for engaging a case on the gas turbine engine.

First claim

What is claimed is:

1. A synchronization ring for a gas turbine engine comprising:
a synchronization ring for a variable vane assembly including a radially inner side and a radially outer side wherein the synchronization ring includes a first annular member, a second annular member, and at least one clevis and the first annular member is attached to the at least one clevis by a first roller bracket and the second annular member is attached to the at least one clevis by a second roller bracket; and
a plurality of rollers attached to the synchronization ring for engaging a case on the gas turbine engine at least one of the plurality of rollers is spaced radially inward from the radially inner side of the synchronization ring.

2. The synchronization ring of claim 1 , including a plurality of roller brackets for attaching at least one of the plurality of rollers to the synchronization ring, wherein the plurality of roller brackets include the first roller bracket and the second roller bracket.

3. The synchronization ring of claim 2 , wherein each of the plurality of roller brackets include a first portion on a first side of the synchronization ring and a second portion on a second opposite side of the synchronization ring.

4. A synchronization ring for a gas turbine engine comprising:
a synchronization ring for a variable vane assembly;
a plurality of rollers attached to the synchronization ring for engaging a case on the gas turbine engine; and
a plurality of roller brackets for attaching at least one of the plurality of rollers to the synchronization ring, wherein each of the plurality of roller brackets include a first portion on a first side of the synchronization ring and a second portion on a second opposite side of the synchronization ring and each of the plurality of roller brackets include at least one cylindrical pivot opening for accepting a pivot fastener and at least one elongated clevis openings for each accepting a fastener, each of the plurality of roller brackets being pivotable about the pivot fastener.

5. The synchronization ring of claim 3 , wherein each of the plurality of rollers is supported by a pin that extends between the first portion of the roller bracket and the second portion of the roller bracket.

6. The synchronization ring of claim 1 , wherein the first annular member and the second annular member extend a first length and the at least one clevis extends a second length, the first length being greater than the second length.

7. The synchronization ring of claim 1 , wherein the plurality of rollers are made of a woven fiber composite.

8. A gas turbine engine comprising:
a fan including a plurality of fan blades rotatable about an axis;
a compressor section including a plurality of variable compressor vanes;
a combustor in fluid communication with the compressor section;
a turbine section in fluid communication with the combustor;
a synchronization ring surrounding the compressor section, the synchronization ring including a plurality of rollers for engaging the compressor section, wherein the synchronization ring includes a first annular member, a second annular member, and at least one clevis and the first annular member is attached to the at least one clevis by a first roller bracket and the second annular member is attached to the at least one clevis by a second roller bracket; and
an actuator mechanically linked for moving the synchronization ring for varying an angle of the plurality of variable compressor vanes.

9. The gas turbine engine of claim 8 , including a plurality of vane arms connecting the synchronization ring to each of the plurality of variable compressor vanes.

10. The gas turbine engine of claim 8 , wherein each of the first roller bracket and the second roller bracket include a first portion on a first side of the synchronization ring and a second portion on a second opposite side of the synchronization ring.

11. A method of varying a vane angle for a gas turbine engine comprising:
rotating a synchronization ring including a plurality of rollers, wherein the synchronization ring includes a first annular member, a second annular member, and at least one clevis and the first annular member is attached to the at least one clevis by a first roller bracket and the second annular member is attached to the at least one clevis by a second roller bracket; and
engaging an outer surface of the gas turbine engine with at least one of the plurality of rollers on the synchronization ring.

12. The method of claim 11 , wherein each of the first roller bracket and the second roller bracket each include a first portion on a first side of the synchronization ring and a second portion on a second opposite side of the synchronization ring.

13. The gas turbine engine of claim 8 , wherein the synchronization ring includes a radially inner side and a radially outer side and at least one of the plurality of rollers is spaced radially inward of the radially inner side of the synchronization ring.

14. The method of claim 11 , wherein the synchronization ring includes a radially inner side and a radially outer side and at least one of the plurality of rollers is spaced radially inward of the radially inner side of the synchronization ring.

15. The gas turbine engine of claim 8 , wherein each of the first roller bracket and the second roller bracket include a first portion on a first side of the synchronization ring and a second portion on a second opposite side of the synchronization ring and each of the first roller bracket and the second roller bracket include at least one cylindrical pivot opening for accepting a pivot fastener and at least one elongated clevis openings for each accepting a fastener, each of the first roller bracket and the second roller bracket being pivotable about the pivot fastener.

16. The method of claim 12 , wherein at least one of the first roller bracket and the second roller bracket include at least one cylindrical pivot opening for accepting a pivot fastener and at least one elongated clevis openings for each accepting a fastener, each of the first roller bracket and the second roller bracket being pivotable about the pivot fastener.

Assignees

• United Technologies Corp

Inventors

• Do Logan H

Classifications

• F01D17/162

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F01D17/14 Primary

  varying effective cross-sectional area of nozzles or guide conduits · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F02C9/20 Primary

  by throttling; by adjusting vanes · CPC title

• F04D29/563

  specially adapted for elastic fluid pumps · CPC title