Variable vane overlap shroud

Patent metadata

Field	Value
Publication number	US-10107122-B2
Application number	US-201414761013-A
Country	US
Kind code	B2
Filing date	Feb 4, 2014
Priority date	Feb 10, 2013
Publication date	Oct 23, 2018
Grant date	Oct 23, 2018

Abstract

A shroud supports one of an inner and an outer trunnion on a variable vane. The shroud is provided by a first and a second axial half. Each of the axial halves is provided by a plurality of circumferentially spaced segments. Circumferential edges are defined on each of the plurality of circumferentially spaced segments. Edges between adjacent ones of the circumferentially spaced segments on the first half are circumferentially offset from the edges on adjacent ones of circumferentially spaced segments of the second half, such that no direct leakage path exists across an axial width of the shroud.

First claim

The invention claimed is:

1. A variable vane assembly comprising:
a plurality of vanes having an airfoil extending between an inner trunnion and an outer trunnion;
an actuator for causing said plurality of airfoils to pivot to change an angle of incidence; and
a shroud supporting one of said inner and outer trunnions, said shroud being provided by a first and a second axial half, with said shroud including a plurality of support surfaces for supporting said one of said trunnions, and each of said axial halves being provided by a plurality of circumferentially spaced segments, with circumferential edges defined on each of said plurality of circumferentially spaced segments, and edges between adjacent ones of said circumferentially spaced segments on said first half being circumferentially offset from the edges on adjacent ones of circumferentially spaced segments of said second half, such that no direct leakage path exists across an axial width of said shroud.

2. The variable vane assembly as set forth in claim 1 , wherein said circumferential edges on said first half is circumferentially spaced from the edges on said second halves by at least a circumferential width of one support surface supporting at least one of said at least one of said trunnions.

3. The variable vane assembly as set forth in claim 2 , wherein there are alignment and securement structures for securing said first and second halves.

4. The variable vane assembly as set forth in claim 3 , wherein there are at least six of said circumferentially spaced segments in each of said halves.

5. The variable vane assembly as set forth in claim 2 , wherein there are at least six of said circumferentially spaced segments in each of said halves.

6. The variable vane assembly as set forth in claim 1 , wherein there are alignment and securement structures for securing said first and second halves.

7. The variable vane assembly as set forth in claim 1 , wherein there are at least six of said circumferentially spaced segments in each of said halves.

8. A gas turbine engine comprising:
at least one of a compressor and a turbine;
said at least one of a compressor and a turbine including a variable vane assembly, the variable vane assembly including a plurality of vanes having an airfoil extending between an inner trunnion and an outer trunnion;
an actuator for causing said plurality of airfoils to pivot to change an angle of incidence; and
a shroud supporting one of said inner and outer trunnions, said shroud being provided by a first and a second axial half, with said shroud including a plurality of support surfaces for supporting said one of said trunnions, and each of said axial halves being provided by a plurality of circumferentially spaced segments, with circumferential edges defined on each of said plurality of circumferentially spaced segments, and edges between adjacent ones of said circumferentially spaced segments on said first half being circumferentially offset from the edges on adjacent ones of circumferentially spaced segments of said second half, such that no direct leakage path exists across an axial width of said shroud.

9. The gas turbine engine as set forth in claim 8 , wherein said circumferential edges on said first half is circumferentially spaced from the edges on said second halves by at least a circumferential width of one support surface supporting at least one of said at least one of said trunnions.

10. The gas turbine engine as set forth in claim 9 , wherein there are alignment and securement structures for securing said first and second halves.

11. The gas turbine engine as set forth in claim 10 , wherein there are at least six of said circumferentially spaced segments in each of said halves.

12. The gas turbine engine as set forth in claim 9 , wherein there are at least six of said circumferentially spaced segments in each of said halves.

13. The gas turbine engine as set forth in claim 8 , wherein there are alignment and securement structures for securing said first and second halves.

14. The gas turbine engine as set forth in claim 8 , wherein there are at least six of said circumferentially spaced segments in each of said halves.

15. A method including the steps of:
providing a plurality of vanes having an airfoil extending between an inner trunnion and an outer trunnion;
providing an actuator for causing said plurality of airfoils to pivot to change an angle of incidence; and
supporting one of said inner and outer trunnions in a shroud, said shroud being provided by a first and a second axial half, with said shroud including a plurality of support surfaces for supporting said one of said trunnions, and each of said axial halves being provided by a plurality of circumferentially spaced segments, with circumferential edges defined on each of said plurality of circumferentially spaced segments, and edges between adjacent ones of said circumferentially spaced segments on said first half being circumferentially offset from the edges on adjacent ones of circumferentially spaced segments of said second half, such that no direct leakage path exists across an axial width of said shroud.

16. The method as set forth in claim 15 , wherein said circumferential edges on said first half is circumferentially spaced from the edges on said second halves by at least a circumferential width of one support surface supporting at least one of said at least one of said trunnions.

17. The method as set forth in claim 16 , wherein there are alignment and securement structures for securing said first and second halves.

18. The method as set forth in claim 16 , wherein there are at least six of said circumferentially spaced segments in each of said halves.

19. The method as set forth in claim 15 , wherein there are alignment and securement structures for securing said first and second halves.

20. The method as set forth in claim 15 , wherein there are at least six of said circumferentially spaced segments in each of said halves.

Assignees

• United Technologies Corp

Inventors

• Maliniak David

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

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D17/12

  arranged in stator parts · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title